Turbo Commander 690-A Training Manual

April 2, 2017 | Author: Andre Peli | Category: N/A
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Rockwell Turbo Commander 690A Flight Safety Training manual...

Description

Rockwell

Turbo Commander 690A Training Manud

General AviationDivision Rockwell Interrethnal

OCM(9-74)

ROCKWELL

COMMANDER

TURBO

MANUAL

TRAINING

The

material

contained

only.

purposes

The contents

the official

publications

Maintenance

Manual,

Flight aid

Manual,

during

Commander

herein

but

is are

are

training

for

intended

not

to supersede

the aircraft: Catalogue,

Parts

to be used courses

to be used

with

Illustrated

the training Training

issued

690A

only

conducted

i.

e. and

as an instruction at

the Aero

Center.

DATED:

October

1,

1974

FOR USE OF THIS MANUAL

INSTRUCTIONS

which are sequenced, This Training Manual into sections is divided possible, closely order of classroom presentation. in A the as as for identidivider with precedes each section quick index tab, page, Each section is identified by a number fication. (i. e. 1. Airframe). identified by Text pages code at the in each section two-digit a are which identifies bottom-right, the Section and Page Number:

Example:

Each

Page Page

1-4 3-5

is Section is Section

with an expanded page is provided will pages carry a notation as

Revised

1, Page 3, Page

right-hand

to the date

4 5

for notes. margin of the revision.

TO SECTIONS

INDEX

Section

1.

Aircraft

Section

2.

Flight

Section

3.

Electrical

Section

4.

Powerplant

Section

5.

Hydraulic

Section

6.

Fuel

Section

7.

Environmental

Control

Section

8.

Miscellaneous

Systems

General Control

System

System

System

System System

t

1-

SECTION AIRCRAFT

1

GENERAL

INTRODUCTION The Turbo high wing, 690A is an all metal, Commander twin engine airplane featuring cabin. Power is a pressurized supplied by two Garrett TPE-331-5-251K AiResearch turbofixed shaft engines, equipped with Hartzell three-blade prop, full-feathering, reversible propellers. Engine constant speed, bleed air is used to air condition and pressurize compressor The airplane is the cabin up to 5. 2 PSI differential pressure. anti-ice for all and de-ice equipped with complete systems fuel cells weather operation. Wing and fuselage are interconnected to form a single tank and store 384 gallons of usable The retractable hydraulifuel. tricycle landing gear is operated with an independent cally and is provided pneumatic emergency baggage extension 600 pound capacity A large volume system. in the center fuselage, below the wing. is located compartment AIRFRAME airframe in three major is manufactured semi-monocoque fuselage, sub-assemblies; (1) forward (2) wing, and (3) aft fuselage. The forward and aft fuselage sections are joined at fuse254, and the wing is attached lage station to load carrying fuselage bulkheads stations 178.81 and 209.15. at fuselage When The

an integral

mating and joining is completed, is achieved. structure

fuselage

and

wing

WING ASSEMBLY The

wing

section is constructed in three sections, center panels. Two built-up the spars are used, having extruded 2014 aluminum caps and 2024 aluminum 160 members. extends from Station The center section panels with the outer Station 160 RH across the fuselage ing from Station AN rivets, 160 to the wing tip. Standard bolts and AN and MS hardware the are used to assemble

the two outer

2014

aluminum forged and lower the to spars rugged attachment. gear

gear

are

surface

to provide

Built-up engine extend mounts are attached to the front spar

A removable equipment

1-2

aft nacelle installed in

an extremely

from the front forward and the wing surface.

assembly

provides

the aft nacelle.

web LH to extendhuckwing.

to the wing

attached

trusses

wing

and

spars

ready

access

and

spar

to

FUSELAGE

ASSEMBLY

airframe

in general is fabricated structure alloy aluminum sheet, extrusions 2014 and 7075 billets using conventional chined and is assembled

The

Skin laps

and

compounds. Manual for The

from 2024, and mafasteners.

seams are sealed with 3-M and Coast pro-seal Maintenance Refer to Section 11 of the Aircraft

sealant

data

and

application

techniques.

by ten bayonet and door is secured type latches, locked mechanism when the aircraft is electrically electrical with system is turned on. The door is equipped seal to retain cabin pressure. rubber The door an inflatable seal pressure regulator below the floor, is located forward of fuselage 69. station cabin

the latch

A plug type emergency door. Cabin pressure the hatch seal to retain

opposite exit hatch is located the cabin helps acting hatch on the to compress cabin pressure.

design cabin interiors are attached to the cabin by channeled Velcro upholand slots, structure tape strips This and of design provides installation stery screws. type and re-installation for airframe as required easy removal service All interior fabrics and inspection. reare flame sistant in accordance with the Federal Aviation Regulations. The

modular

floor incorporates The fuselage through which a tunnel-way fluid flight control cables, hydraulic is routed primary the lines and other fluid or pneumatic lines. The enpressure "Controlex" cables and these are gine controls are flexible routed along the windshield centerline of the center post, leading edge wing and out fuselage through the upper to the engine section. laminated The windshields plate glass are Pittsburgh heated. The cockpit side windows and electrically and eyebrow windows plexiglass. The pilots side are single pane acrylic window direct vision window. Double incorporates or vent a acrylic plexiglass windows featured in cabin. the pane are This provides structural redundancy and the air gap between and noise suppression. the panes provides thermal insulation

"aircon"

Load

structural bulkheads carrying in the tail cone provide attach horizontal for and vertical flight structure the the surfaces. flight dual spars, These surfaces incorporate interconnecting ribs and stressed skin.

CORROSION

CONTROL

fabricated parts Commander are treated to resist airframe insuring increased corrosion, service thereby preventative life and reduced The maintenance costs. control is cleaning and etching corrosion by started process The immersed parts. parts into the fabricated are then an solution. This leaves base film coating a chromic This is followed up by a zinc-chromate spray on the parts. of the painting. All these steps are taken prior to assembly The completed aircraft is cleaned, exterior component parts. bath, air dried, and given an alodine then primed spray paint. with painted

Aero

"alodine"

"alumigrip"

1-4

19'

.

Rockwell

Turbo

Commander

46'

l'

-

-

-

9. 30"

690A

6. 64"

2. 24" 15'

5'

-

-

5. 00"

14'

-

11. 35"

7 00"

44'

-

4. 25"

1-5

23'-3" 81'-10"

58'-7"

35'-4"

27'-0"

22

Figure

1-6

1, Minimum

Turning

Distances

23

ENGINE TACHOMETER

20-'-

,6

4

oo 't,,

-

5 40 50

70

so

96-100%

:

PERCENT

80

~

-101%

NORMAL MAXIMUM

Green Arc Red Line

RPM RPM

,

\' ,

28 6

INTERSTAGE TURBINE TEMPERATURE 923°C 1149°C

GX 100 54 30FF

'//76

Red White

TAKEOFF START LIMIT

2837

ENGINE GAGE OIL TEMPERATURE -400C +55°C +55 +93°C +93°C OIL PRESSURE 50 PSI 50-70 PSI 70-120 PSI 120 PSI FUEL PRESSURE 15 PSI 15-25 PSI 25-80 PSI 80-90 PSI 90 PSI -40

-

-

••

es

, *

*

""

Figure

1-2. Instrument

Markings

(Sheet

UNIT

Red Line Yellow Arc Green Arc Red Line

MINIMUM CAUTION NORMAL MAXIMUM

Red Line Yellow Arc Green Arc Red Line

MINIMUM CAUTION NORMAL MAXIMUM

Red Line Yellow Arc Green Arc Yellow Arc Red Line

MINIMUM CAUTION NORMAL CAUTION MAXIMUM

1 of 3)

FAA Approved

1-7

\ KNOTS

\260 aso

40

300 2oo ISO

AIRSPEED

60

60

250

AIRSPEED

---

77

2o

MPH 160

/

40

-

go

ioo

82

160 14o

-

86 140 115 243 243

Knots Knots Knots Knots Knots

Red Line White Arc Blue Line Green Arc Red Line

MIN S. E. CONT. FLAP OPER BEST S.E. ROC NORMAL OPER MAX OPER

N

ioo

2817

HYDRAULIC PRESSURE -o

2ooo-

1250 PSI

HYD PRESS

28

VACUUM N

10

28

Figure FAA Approved

1-8

3. 8 IN. Hg 3. 8-5. 0 IN. Hg 5. 0 IN. Hg

..--

o

MAXIMUM

3

upii

.se

Red Line

Red Line Green Arc Red Line

3

1-2. Instrument

Markings

(Sheet

2 of 3)

MINIMUM NORMAL MAXIMUM

EMERGENCY GEAR EXTENTION

iooo 500

A IR 425 PSI 425-525 PSI 525 PSI

LBS PER SQ lN 2000 o

Red Line Green Arc Red Line

MINIMUM NORMAL MAXIMUM

283

',

so

ALTITUDE AND DIFFERENTIAL PRESSURE

"

DIFF PRE

I5'

40

\

/

5.4 PSI

Red Line

MAXIMUM

20

3025,

17

28

\ ,

4

3,oomm 5

2

"/ 6

7,

SHAFT HORSEPOWER

=

717. 5 HP

Red Line

MAXIMUM

H.P. X 100 28

10

Figure

1-2. Instrument

Markings

(Sheet

3 of 3)

FAA Approved

1-9

ELECTRICAL

LIGHTS

GENERATOR EXT

BATTERY

PWR

L

BUS CONTROL

R

TlE

DOOR

DISTR

BELTS NO SMOKE

LOCK

CABIN

CABIN

PANEL

POS

ANTI-COL

STROBE

PAR-

° F F

NTS

GND START

TE5T SER-

OFF

-

-

-

OFF/RESET

OFF

-

OFF

OFF

UNLOCK

L

BELTS

R

OFF

OPEN

LEFT ENGINE HP

IT

L

FUELNPUMP

FUNEL

VNRD

LANDING

HMYDR L

AIR

EXTEND

5T

GND

O

O

OFF

PUSH

FOR

GND

START

EMER OFF

MOTOR

DO

ICE PROTECTION L

ENG

W5HLD LOW

RUDDER

L

INLET

PITOT R

-

L

FUEL

VENT

R

NOT

-

R W5HLD

INLET

INVERTER

AMP5

O

F

F

F

F

F

F

OFF

1

l

LOW

PROP

RADIO 2

SPKR

AUTO

AMPL

PILOT

O

PROP

HIGH

2

GEN

OFF

-

EMER

---

OFF

OFF

WIPERS

RIGHT ENGINE

BOOT5

WING

DEFOG

LIGHT

ONECY

BLOWER

FUEL-HYDR NORM

IGN OVRD

HP

FUELPUMP ON

AIR

-

L

FA5T

PARK

SLOW

R

EMER OFF MAN

-

OFF

-

MOTOR

PUSH

FOR

GND

START

Overhead

DIMMER-

LIMIT

TEST

OFF

Switch Panel

PARK

RETRACT

EXTEND ABOVE 156 KNOTS

AVIONICS GEN

O

HIGH

OFF

-

OVHD-5UB

SECTION FLIGHT

2

CONTROLS

INTRODUCTION control The Turbo Commander is equipped with dual flight pedals, permitting columns and dual rudder/brake them to be controlled The from either seat. the pilot or co-pilot elevators, rudder and left aileron with conare equipped balanced", assembly The rudder is trollable trim tabs. and the slot between horn and the vertical stabithe rudder lizer is thermally de-iced. The wing flap is single slotted mechanically interconnected, of four sections type, consisting and hydraulic actuated. pressure

"horn

CONTROL

COLUMNS

columns constructed from magnesium Two flight control aluminum alloy tubing are attached and castings to the airroller bearings. craft floor by pillow blocks and structure The control mechanism contained inside each column conmounted Turnand ball bearing sprockets. sists of chains buckles for tension and rigging adjustments. are provided AILERON

CONTROL

(See Page

2-4)

The all metal

ailerons to the aft wing spar at are attached with sealed bearings and are 100¶o statically points of the control wheel moves balanced. Rotary movement a pulleys, bellcontrol cables, sprockets, system of chains, under columns rods from the control cranks and push-pull compartment, the floor to the aft side of the baggage up and belleranks. A out through the wing tunnel to the aileron cable is connected balance between the right and left aileron belleranks Two turnbuckles to complete the system. are cable located in the baggage while the balance compartment nacelle turnbuckle is in the left wing area.

three

RUDDER

CONTROL

(See Page

2-5)

pedals enable the pilot and co-pilot to brakes A system of and nose steering. pilot co-pilot rudder and connect tubes the pedals A rudder cable is attached together. to each inboard aft through the pedal horn under cabin floor, the then passes fuselage rudder assembly which is connected to a torque tube base of between rudder. A balance cable is connected the to the Dual

rudder

control

control the rudder, concentric torque

2-1

(Continued)

CONTROL

RUDDER

the front side up and across the pedals and routed forward, complete forward Three cabin bulkhead the system. the to of and which provide adjustment turnbuckles tension, two are and one in the top of the nose located in the lower aft fuselage of

landing

gear

ELEVATOR

wheel

well.

CONTROL

(See Page

2-6)

by fore and aft movement of the The elevators are operated control column. cast At the base of each column magnea below the cabin floor. Attached sium arm extends to the push-pull The push-pull rods. rods arms are adjustable between floor beams. aft to a transfer extend tube mounted Cables connect the forward transfer tube to a transfer tube push-pull rods attach in the aft f uselage. Adjustable the aft Turnbuckles in the aft transfer tube to elevator tube. torque coil fuselage provide adjustment and tension. Four large holding down action provide springs the elevators a bungee while the aircraft is on the ground and provide better elevator single engine operation. balance during stalls and slow speed .the

TRIM

(See Page

2-7)

and elevator The rudder trim tabs are mounted on the trailing surfaces. Tab movement control is edge of their respective accomplished by rotating hand wheels, of drums, system a pulleys, chains, flexible shafts and screw cables, jacks provide the necessary movement. Adjustable trim tab turnbarrels Electrical in the aft fuselage. for the cable systems are located position mounted adjacent tab trim transmitters to their re spective trim tabs actuate trim tab indicators on the instrument The left aileron panel. actuator, tab is driven by an electrical mounted in the left aileron.

WING FLAP

CONTROL

flaps are hinged Two all metal attached to brackets to the rear each wing. The flaps controlled by a lever of spar are on the control pedestal by a single hydraulic engine and actuated cylocated linder in the aft fuselage. of sheaves and A system cables interconnects The cockpit control lever the four flaps. "UP", "DOWN" provides and "NEUTRAL", three selections, infinite of flap position selections thereby permitting throughelectric flap out the operating position An transmitter range. in the aft fuselage indicator actuates a flap position on the inpanel. Two flow valves mounted in the hydraulic strument lines adjacent cylinder provide slow and smooth to the actuating flap travel.

2-2

TURNBARRELS SLAVE SHEAVE

ACTUATING CYLINDER WING FLAP FLOW CONTROLVALVE

MASTER SHEA E

HYDRAULIC LINES TO LANDING GEAR FLAP CONTROL

AND WING VALVE

LANDING GEAR AND WING FLAP VALVE CONTROL 27

Flap

Control

37

System

2-3

INSPESCTA

BELLCRANK

°

G

MECHA

PULLEY

AILERON PUSHPULL

ELEVATOR

CABLE DRUM

PUSH-PULL ROD

ROD PULLEY

BALANCE TURNBARREL

CABLE

TURNBARRELS

2732

Aileron

2-4

Control

System

TURNBARREL

BALANCE CABLE

TURNBARRELS

ACCESS

DOOR

CE CRENMNOE R

RU

UEDRDEE R

D RUDDER T UBE

TORQUE

o

\ DR NL R

TORQUE ARM

AL

RE

27

Rudder

Control

4

System

2-5

SEE DETAIL B

/

TURNBARRELS

SEE DETAIL A 2734

ELEVATOR FORWARD

TRANSFER TUBE ELEVATOR

TORQUE TUBES ELEVATOR STOPS CONTROL COLUMN

'

\

PUSH-PULL

'

'

ROD

'

IDLER PULLEY PUSH-PULL

ROD

IDLER PULLEY

AFT

TRANSFER TUBE ASSY

ELEVATOR BUNGEE SPRINGS

276

Blevator

2-6

Control

System

27,

SEE DETAIL B

TURNBARRELS

SEE DETAIL A

27 35

ELEVATOR

TRIM TAB

0

ROLLER

CHAIN

BRACKET CABLE DRUM

ROLLER

CHAIN

GEAR AND

PINION

.

ELEVATOR o

/

TRIM TAB

o

ELEVATOR TRIM TAB WHEEL

ELEVATOR INDICATOR

TRIM TAB TRANSMITTER

27 7

27 7

Elevator

Trim Tab Control

System

2-7

SYSTEM

3

ELECTRICAL

GENERAL

SYSTEM

DESCRIPTION

The electrical is designed supply system to provide an abundant regulated direct for operation of voltage of current power the The primary aircraft various systems. components are two Nickel-Cadmium batteries, storage two engine driven starter/ split bus distribution The system with a system. generators automatically devices which disconnect load sensing incorporates fault. overload and isolate any

BATTERIES 40 ampere batteries at 24 volt, The 20 cell air cooled are rated designed and are specifically for jet engine hours, For starts. loads of 1000 amps or more momentary this purpose, may be cells The nylon case battery drawn from the battery. are packed lined stainless The manufacturer's in a neoprene steel case. instructions adhered must be rigidly the batto when servicing The batteries with a temperature monitor, tery. are equipped isolation switch. Refer indication and battery temperature to airplane Flight Manual for test and operating procedures. STARTER/GENERATOR starter/generators 6650The air cooled are wide speed range, for 300 amps 26 volts with 1. 25 ohms in exciter 12000 RPM, rated by Lear Siegler, field. The units are manufactured and are clamp drive pad adaptor. mounted Routine maintenance on to an engine brush and commutator involves The generator is servicing. equipped with internal filters. radio noise -

VOLTAGE

REGULATORS

Electric carbon pile voltage regulators, mounted in the aft fuselage, voltage. regulate used These output generator to are regulators calibration have voltage should adjust be pots and set at 2 28. 7 + and engines VDC when at operating temperature running at 96% RPM. The regulator base assembly contains the generator load paralleling adjustment The generators be should pot. load paralleled within 30 amps.

General

.0

-

.

3-1

D.

C.

BUS AND CONTACTOR

BOX

This box assembly, is designed mounted in the aft fuselage, centrally locate, house and protect the heavy duty battery, relays, relays and starter plus engine control start generator miscellaneous equipment. All and other electrical system wire supports and ties in this box must terminal connections, be kept secure, objects. and the assembly free of foreign identifications in the box, and a layComponent are stenciled identification out diagram may be found in Section X of the Manual. Maintenance

SPEED

ELECTRONIC

to

SWITCHES

receives The engine speed sensor an input front the engine is calibrated for three driven This sensor tach-generator. signals RPM's. These signals selected output engine output at referred 3, 1, No. 2 and No. switch No. occurto as speed are ring RPM. The in sequence at 10%, 50% and 90% of engine is used in the electrical speed autosystem to provide sensor functions. of certain Field starting matic sequencing engine repair assembly. is not permitted sensor on the speed

BATTERY Refer

AND

to Figure

BUS SYSTEM No.

1, Page

3-7

design incorporates The system main bus, a battery-generator bus and start auxiliary bus. Through engine start an external receptacle be powered from an plug bus start may the power If batteries and external is external unit. am on power power applied, parallel with external operating in unit is the the power batteries. Through circuit breakers, heavy duty remote reset via a distribution electrical is supplied loads power to airframe bus. bus and a control The batteries by a BATTERY are controlled however, BATTERY SELECT switch on a pedestal position must be in the NORMAL on.

MASTER switch; engine lever the power have both batteries to

of the battery Activation is accomplished in the following system When BAT MASTER SW is turned on, electrical the sequence. from No. 2 battery Al of BLC-2 at terminal is routed power diode through a to a terminal post and to terminal X1 of BLC-2. Another wire attached to terminal X1 of BLC-2 is routed through D2-D3 of SR-2, also terminals D2-D3 of SR-1 and to terminals X12 of BSC, This terminal X1 and then to terminal X1 of BLC-1. voltage for battery is the control circuit BSC BLC-2, contactors

3-2

BATTERY

AND

BUS SYSTEM

(Continued)

for BLC-2 is The electrical ground path circuit closed 5-6 of X2 through the normally terminals SW to the BAT MASTER SW. The electrical the BAT SELECT X2 of for BSC and BLC-1 is from terminal ground path circuit 1-2 of BAT BLC-1 to terminal X2 of BSC through terminals SW. SELECT SW to the BAT MASTER When these contactors No. 2 battery BLC-2 connects to the main bus, are energized, and BSC connects No. 1 battery to the start bus and BLC-1 Thus the two batinterconnects the start bus and main bus. in parallel. teries are operating and

BLC-1.

from

terminal

SW combines POWER SELECT The START first two functions; OFF-ON switch, secondly it it functions power as an external parallel battery configuration is used to preselect for or series engine from aircraft batteries. Note: starts Always follow airfor engine starting. plane Flight Manual The seriesprocedures 3-1. parallel battery control circuits can be seen on Figure X1 of BSC. There at terminal terminating are two circuits SELECT SW is 24VDC power on one pole of the START POWER BAT start applied to terminal X1 of BSC when EXT PWR/PAR battery holding circuit This provides is selected. a parallel When a series for BSC and BLC-1 during battery engine start. is selected control circuit eminating from start the BSC-BLC-1 by the engine relay start terminal X1 of BLC-2 is interrupted (SR-1 or SR-2) causing Thus No. 1 BSC and BLC-1 to drop out. from the bus is isolated is disconnected and the start battery main bus. Then an electrical start signal from the engine con12-13 of BLC-1 to terminal tactor is routed through terminals X11 of BSC. battery provides This action input power a series relay and start overvoltage An overvolt sensor to the start bus. (SOVR) are incorporated applied to limit start bus voltages to the START AUX BUS. (RCB-2) breaker circuit reset on the main bus is the of electrical distribution bus and power to the aircraft of electrical auxiliary bus is the source power on the start control bus. Each segment of the distribution or to the aircraft control bus is limited loading by circuit breakers and to 35 amperes bus transfer load is limited by the bus tie circuit to 20 amperes breakers.

A remote source RCB-1

ENGINE Refer

STARTING

to Figure

No.

SYSTEM 2, Page

3-8

The engine control circuits and aircraft fuel supply start circuits are integrated switch controls the starting so that a single of the turboprop engine. The engine lever is power or shutdown positioned flight for all ground starts. idle position at The engine

3-3

ENGINE

STARTING

SYSTEM

(Continued)

lever The is positioned at low RPM for starting. profile crank engine with engine is start general the the to and fuel are starter In doing so, ignition up to 50% of RPM. automatically sequenced is turned on at 10% RPM and ignition released The engine at 50% RPM. off and starter then acce1erates For all on to idle RPM on the gas turbine energy. blades propeller Zero at ground starts secured the thrust are pitch angle by ground start propeller blade latches. condition

The electrical relay sequencing for starting the engine occurs diagram). When the order schematic in the following (follow switch -FUEL boost engine rotated ON-, start the pump to (BPR) relay is energized and fuel at boost pump pressure, 15 PSI minimum is supplied to the engine fuel pump adaptor. (SAR) is energized The start auxiliary relay and through the "A" and "B" poles arms (SR) and circuits relay start the to (FR) to field relay the generator through "C" pole causes break" before switch Rotating energize. start the to completes AIR START the circuit through SS-2-50% speed (SR), and from switch, and "B" pole of SAR to the start relay SR through "A" pole of SAR to terminal X1 of SAR. This action and provides holding circuit energizes relay start the to SAR a while engine RPM is below 50% RPM.

"make

relay start through pole "A" arms the ground start circuit, propeller unfeathering through pole "B" causes pump to operate (IR) circuit. and through pole "C" arm the ignition relay If inflight will spool windmilling propeller air is start this the an the engine RPM up. When engine RPM increases to 10% SS-1 (IR). will close and energize ignition relay The IR "A" pole the electrical circuit completes ignitor unit, engine the power to the The

(SPR). fuel valve and start relay The SPR "A" engine pressure pole supplies fuel regulator. Engine start power to the pressure should light off and accelerate with windmilling propeller assist. 50% RPM, WhenRPM increases SS-2 opens. to approximately is The ground start This deactivates all start circuits. sequence fine propeller is latched in air start except that the the same as motor pitch and the starter engine when the is used to crank START. switch is rotated GROUND start through the to Flight Manual procedures for engine Note: Always use airplane starts.

"detent"

"light-off"

Motoring by is accomplished the engine without holding override switch and placing in motor position the ignition (EMR), The engine relay motor the start switch at ground start. when energized, circuits fuel interrupts start pressure to the regulator, engine fuel valve and ignition vibrator, thus fuel and ignition chamber. are not admitted to the combustion

3-4

GENERATOR Refer

to Figure

SYSTEM No.

3,

Page

3-9

includes The generator system two engine driven 300 amp D. C. starter/generators, relays, current two reverse two Hartmann carbon Electric pile voltage regulators and control General recharacteristics lays necessary switching the desired to provide off information by a and fault protection. is provided Generator panel. monitor light in the annunciator voltage regulators and lead paralleling adjustments The generator Manual shall be set in accordance with the airframe Maintenance The carbon regulators procedures. pile voltage must be at operaregulator adjustments. The voltage when making ting temperature be 28. 7 +. 2 VDC when 20 cell batteries setting should are relays should be set at 30. +. 9 VDC. installed. The overvoltage -.0

engine start the field relay (FR) is energized to open the field circuit. This automatic safety circuit protects when the starter-generator is being used as a high torque the system cranking motor. start is completed, After engine the field relay will automatically de-energize. During

generator

field circuit The generator is traced from GEN terminal on the (RCR) relay (CS) current current through sensor reverse to B2of the field relay and L+ of voltage A2 terminals G terminals to regulator regulator and from F+ on voltage to A terminal on field winding generator terminal block and through generator to E terminal circuit is output voltage Generator ground. this on (GCR). relay applied control The to X1 terminal of generator switch when turned "ON" provides master ground generator a If external for the generator control relay. power is off, when control relay from is completed is energized, the generator a circuit of FCR to the switch of GCR through B2-B3 A2 terminal terminals (SW) terminal of the reverse relay. If generator voltage current is 3 to 6 volts higher the RCR will close than main bus voltage, signal connecting the generator to the bus and a D. C. voltage (IND) terminal from the RCR indicator will cause the GEN-OFF light on the annunciator panel to extinguish. .

.

GENERATOR

FAULT

PROTECTION

fault protection includes (1) undervoltage, (2) overvoltage, feeder fault, and (4) field fault. The reverse will relay current disconnect if it goes undervoltage. A field fault or the generator feeder fault or overvoltage fault would allow the field control relay energized. When this occurs, FCR automatically to become turns off, opening The FCR picks up the generator the B2-B3 contacts. circuit and the generator through the A2-Al contacts a holding

Generator

(3)

3-5

GENERATOR

FAULT

PROTECTION

(Continued)

Of course, light will be illumiswitch. master the GEN-OFF annunciator nated on the panel since the reverse relay current The operator under is also de-energized a fault condition. should and if it will not attempt to reset the failed generator he should satisfactorily, failed switch reset generator turn the Flight Manual off and follow airplane procedures pertaining to generator. a failed

Refer

to Section

maintenance

3-6

and

X of

the aircraft troubleshooting

Maintenance procedures.

Manual

for

service,

BUS TlE N/O

24V STA RT C.B. START POWER SELECT

DISTRBUS 20

SW OFF

ON '

g

'

3EXIPW. PARBAT

AT

BUS "CONTDISTR 35

ISTR RESET

BAT

e

SELECT

N/O BUS TIE

35



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SEOR

BS

CONT BUS)

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RESET

CONIBUS 35

a

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MAIN BUS

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550°C ITT

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ENGOFF FUEL ON

IGN O VRRD

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--

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SS-2 50 ON

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Reset CB

Bat/Gen RCR SOVR

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BLC-2

GSC-1 S/Gen

Volt/Reg

Ma n Bus

BLC-1._

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FR

GSC-2 Engine

Start

Bus

a S/Gen EPC

Bat-1

BSC

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--

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Bat-2

26VAC OXY

LT AUX

ANN 3

HDG2

RMI

NAV1

COM1

ATC1

AUDIO

TRIM

A/P

Y/D

ADF

RADAR

MFD

TCAD

ADC2

HF

ALTM

FUEL

ADC1

AHRS

PFD

FIRE EXT OIL DOOR

INV

GYRO 2

COM 2

UNFEATHER

INV

5 VT

2

LTG

ENC1

FLOW

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NAV 2

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F

SECTION

4

POWERPLANT

INTRODUCTION The fixed shaft turboprop engines in the Model AiResearch. manufactured by mander Garrett are is designated Model TPE 331-5-251. This as a horsepower engine, box limited and rated gear facturer The engine incorporates to 725 SHP. box, two stage centrifugal three compressor, bine and a single annular combustion chamber.

690 Turbo ComThe engine is an 840 shaft by the manuan integral gear stage axial tur-

shaft power The turboprop engine produces rotating to drive a propeller, and the accessories for engine and airnecessary heat by converting The engine craft operation. produces power combustion in into rotating mechanical the energy energy gases in the gas turbines. Ambient air is drawn in and compressed by a two stage centrifugal The compressed air compressor. plenum, is collected and delivered in a combustion the to annular combustion chamber where fuel is added and atomized high temperature ignited. The expanded combustion gases are routed imparting stage turbine the three to energy to the turbine wheels, which drive and the reduction the compressor gear train. Spent gases coming off the turbine are delivered back to atmosphere by an exhaust This gas flow creates tailpipe. jet a slight See Figures 4-1, 4-2 and 4-3. thrust. control The principal engine components are the fuel control (Bendix propeller oil transfer DP-K2), pitch control tube servo, operations, and the propeller During ground the fuel governor. maintains required engine speed by moduunderspeed governor fuel flow to the combustion chamber in response lating to engine of the propeller load changes pitch controller caused by movement During flight for forward operations thrust power. taxi or reverse fuel is scheduled lever and the propeller by the power governor propeller blade pitch angle. maintains engine speed by modulating

MOUNTING

PROVISIONS

which are structurally attached primary engine mounts, to isolating of vibration consist system, three torque spar These mounts. are adapted to the engine reduction gear housing. A fourth mount attaches All the turbine case to the nacelle. engine refer mounts must be kept in good condition, to Airframe Maintenance Manual for engine mount installation torque valves. The

the wing

4-1

P1 Ambient

T1 Ambient

Pressure

P2 Compressor

Inlet

P3 Compressor

Discharge

Pressure

P4 Turbine

Inlet

P5 Turbine

Discharge

Pressure

Pressure Pressure

Temperature

T2 Compressor

Inlet

T3 Compressor

Discharge

Air

T4 Turbine

Inlet

T5 Turbine

Discharge

Temperature Temperature

Temperature Temperature

FUEL

l

AMBIENT P1 T1

P3

AIR

DRAWN IN

a

COMBUSTOR

T3

P2

F

2

REDUCTION GEARS

ENGINE STATIONS AND

BASIC GAS FLOW

Figure

4-2

T4

TURBINE

COMPRESSOR

OS

PA

4-1

--

P5 T5

REDUCTION GEAR SECTION

TURBINE SECTION

COMPRESSOR SECTION

INPUT

HOUSING ASSEMBLY INTERMEDIATE GEARBO× HOUSING-

ACCESSORY MOUNT PADS CURVIC COUPLING

En

COMBUSTION CHAMBER

PROPELLER SHAFT FIRST STAGE MPELLER

o

SECOND STAGE

-STATOR ASSEMBLIES

TURBINE PLENUM ASSEMBLY EXHAUST PfPE ASSEMBLY

IMPELLER

TS QUE ASSEMBLY

o

o

HELICAL DRIVE GEARSHAFT

OUTPUT HOUSING ASSEMBLY

'

uLCET MAIN SHAFT

MATCHED HELICAL GEARSHAFT SET (HIGH SPEED PINION) F-44A-20385

i CD

TAIL CONE

TORSIO SHAFT COMPRESSOR HOUSING ASSEMBLY

TRANSITION LINER ASSEMBLY

FIRST STAGE TURBINE WHEEL

SECOND STAGE TURBINE WHEEL

THIRD STAGE TURBINE WHEEL

\d

s

4-4

Figure

4-3

í

ENGINE

COWLING

enclose A nose cowl and inlet duct assembly the forward porcowl panels metal covering tion of the engine with removable installation. panels of the engine Suitable access the remainder for adequate engine A small servicing. access are provided door is provided for lubrication oil tank dip stick and filler. IGNITION

SYSTEM

ignition coil is a 4. 65-joule, radio-noise suppressed, highcapacitor-discharge dual output type which provides The input of from for firing plugs. 10 to 30 volts two igniter vibrator mechanically interrupted de is by the the to achieve The action necessary transformer the voltage. to increase from the transformer secondary current through a passes rectifier and is stored in a tank capacitor. Since the rectifier characteristics, exhibits undirectional will not the current flow back through the transformer secondary to ground, but is stored in the tank capacitor until a voltage level equal to the voltage ionization of the trigger discharge When gap is reached. it changes from device to a conductthe gap ionizes, a blocking from the tank capacitor The first ing device. of current surge flows through the primary of the high-tension and transformer This spike of current into the high-tension capacitors. raises in the high-tension secondary the voltage transformer to approxi18, 000 volts, which in turn ionizes mately the air gap in the spark igniter. With both the trigger air gap and the two igniter in the tank state, the remaining energy gaps in a conducting capacitor is placed where of the spark igniters the airgaps across it ignites mixture in the engine combustion chamthe combustible ber. The

voltage

The output circuit contains in operation of one igniter be open or short-circuited. The

duty

cycle

for

the ignition

(1)

1 minute

(2)

2 minutes 2 minutes

on on

5 minutes

on

(3) The igniter high-voltage bine casing.

a divider

the event

on

1 minute

-

plugs are of applications.

coil

-

-

-

network

which

that the other

the assures should output

is as follows: off.

2 minutes off. 23 minutes off. 55 minutes

off.

the air-gap

type and are

The

are

igniters

locat

designed ed on

for

the tur-

4-5

IGNITION

SYSTEM

(Continued)

discharged from the ignition unit is applied to the electrode plugs, of the igniter forming center potena voltage between electrode and electrode. center grounded tial the the When the potential between reaches the electrodes a sufficiently The remainhigh level, air separating is ionized. the them gap ing electric charge in the ignition coil discharges the across electrode ionized and creates a high-energy gap to the grounded spark.

Current

The

body of the plug is cooled discharge by the compressor air liner. This air surrounds combustion enters that the through four holes covering in the base of the shroud end the inserted of the plug. The air then flows under shroud, along the the body of the plug, and out the tip. from the ignition The high-tension leads coil Lead sufficiently flexible plugs bending igniter permit to the to are Each lead is covered with a metallic for installation and removal. wire braid. Care should be taken during installation to prevent leads. chafing of the high-tension Ignition

-

by an engine speed switch The ignition system is energized and override switch in the cockpit) at 10% (or by an ignition It is switch is turned off by another engine at 50% RPM. plugs be removed recommended and cleaned that the igniter 200 hours. replaced every

LUBRICATION

or

SYSTEM

90 to 120 psi pressure pump developing lubrication for the various engine gears Three and bearings. in the reduction two scavenge pumps, gear section and oœ in the turbine section, oil to the oil tank. return normal of the scavenge The capacity is such that during pumps engine operation of inside engine operates at the the pressures less than atmospheric. is installed An oil vent solenoid on the RH forward portion of the gear case. The valve is opened when break suction is oil starter the the turned on to pumps on the easily in cold thereby allowing the engine to be motored more weather. In addition providing lubrication for various to the lubricating oil is also used for propeller actuation components, The oil tank is mounted and by the torque sensing components. right side of the reduction The oil on the lower gear section. full mark 6. 00 contains when level quarts at is tank the the on When the level is at the add mark, the dipstick. the tank conoil. Use turbine Type I or Type II synthetic tains 5. 00 quarts.

An internal pressure provides jet and mist

oil is accomplished by the use of a conventional lower oil heat cooler mounted behind and fuel firewall the a installed valve exchanger in the oil tank. bypass A thermostatic

Oil cooling

4-6

SYSTEM

LUBRICATION

(Continued)

in the oil cooler the oil from passing to prevent 1800F. reaches the cooler until the oil temperature side of the reA bypass type oil filter is mounted on the right is installed

through

and it should be serviced in accordance duction gear housing If the oil procedures and intervals. with approved inspection should become filter obstructed to the point that the bypass indicator pin will be exposed opens, on the bypass a bypass filter valve. pin after is replaced. The filter Reset indicator by unscrewing ring, is removed the adaptor then removing the filter housing. When reinstalling the filter, use new packings element and housing. on the filter When preparing to change engine oil and prior to removing which are located portion the drain plugs, on the lower.forward plug) of the reduction housing magnetic base and at the (a gear of the oil tank, it is necessary the propeller to feather to redome. move the oil from the propeller

ENGINE

FUEL

SYSTEM

of the engine fuel system components are the infuel high boost jector type pressure pump, pump, vane type indicator), bypass bypass valve filter and (incorporating a valve, T2 inlet sensor, fuel control, bypass torque limiter regulator, fuel pressure flow divider fuel shutoff valve, start manifolds primary and secondary and nozzle and drain valve, aircraft, assemblies. Prior starting boost to the the pump is turned on, fuel is then supplied into the engine mounted The high pressure is routed output jector pump. pump to the fuel control. Fuel flow to the engine is restrained by the closed valve opens valve. fuel shutoff The fuel shutoff at approximately 10¶o engine fuel to enter and permits speed and the flow divider drain valve. The drain valve closes and fuel is routed the to fuel manifold and nozzle assemblies for primary and secondary (See Figure 4-4). combustion. The

Fuel The

major

Control Bendix

fuel control overspeed contains an engine engine underspeed (USG), main governor metering valve and a bypass valve. Basically the bypass valves function fuel pressure regulator by maintaining as a metered drop across valve, and the main metering pressure a constant (See figure bypassing surplus pump output back to pump inlet. 4-5).

governor

Inlet

DP-K2

(OSG),

Sensor

A TS-R1 temperature inlet inlet air senses

compensator

temperature

located in and provides

the engine

air a compensated

4-7

I

oo

Engine Boost Pump

High

Press Gauge

Press Pump

Start Press Regulator

Filter

Flow Rate Gauge

Primary Manifold

Flow Divider / Drain Valve

O

§ Nozzle

-

Tank

trol Boost PumP & Fuel Valve

Fuel Shutoff Valve Eypass

Return

Line

Torque

Eypass

Limiter Valve

.....(-)

Fuel Heater

-C") Secondary & Nozzles

Manifol

Inlet

(Continued)

Sensor

The two units function signal to the fuel control. fuel fuel schedule for control determines thusly; the the proper engine established by the the power required the to provide as control levers. The TS-R1 engine compensator temperature schedule of the fuel control alters the maximum to compensate inlet Engine variations for in compressor air temperature. changes inlet characteristics in air temperature; vary with fuel schedule must be altered therefore, the maximum to prestall and excessive vent compressor turbine temperature. pneumatic

Start

Fuel

Regulator

fuel control. during engine of fuel supply deactivated at

The

start

the fuel

Fuel

Shutoff

regulator with is plumbed in parallel pressure regulator only This fuel pressure functions for the purpose of assuring start an adequate for light-off and accelerating It is the engine. 5500 ITT, within by circuits the ITT instrument.

Valve

fuel valve acts as a fuel shutoff in the metered The fuel shutoff line to the nozzles. The valve is a dual solenoid type and is mechanically latched in either position. the fuel-on or fuel-off solenoid is energized The fuel-on speed by the 10% RPM engine solenoid switch override switch, and the fuel-off is or ignition energized by placing switch at engine-off the engine control position.

Flow

Divider

and

Drain

Valve

fuel to the primary The flow divider and drain valve directs fuel manifold Initially and secondary and nozzle assemblies. fuel flows through the primary primary manifold port to the fuel flows and nozzles during starting. rises, As fuel pressure manifold and nozzles, port to the secondary through the secondary manifold assemblies and secondary and nozzle now both primary fuel requirement. On the increasing are operating to provide shutdown, loaded engine drain valve will open and the spring manifolds draining vent primary and secondary to atmosphere, the fuel from these manifolds. Fuel

Manifolds

manifold The primary supplies five fuel nozzles cirmounted cumferentially around chamber. The secondary the combustion manifold supplies axially mounted around the ten fuel nozzles aft end of the combustion chamber. The fuel nozzles should be checked and cleaned in accordance with engine Maintenance Manual requirements and schedules.

4-9

Torque

Limiter

receives The torque limiter computer a signal from the engine The torque limiting computer accepts the tortorque sensor. computes the transducer, que signal from the torque pressure

and (if limits generates error, are exceeded) a corrective signal action This electrical is converted signal. to mechanical motion by the torque motor bypass valve assembly, which fuel back to the fuel pump then bypasses some of the metered of 120 PPH), inlet (up to a maximum engine thereby limiting also furnishes The torque transducer torque. a torque signal in the cockpit. indicator to a shaft horsepower

limiting incorporates system an ON/OFF/TEST A limiter function will verify switch. satisfactory torque test operation of the system. With condition lever ín low RPM and depress lever in flight idle, test switch and note a drop power If the system is inoperative, place in fuel flow. switch in OFF position and the operator must monitor tor ue limit as well as will If system ITT limit. is operative and "ON' the operator other engine and monitor ITT limit need to observe gauges. The

torque

,

Fuel

Control

Characteristics

device The Bendix DP-K2 is a mechanical incorfuel control fuel bypass fuel metering valve, engine valve porating and a driven speed Functionally it sensing flyweight governors. pneumatic fuel contains section. Figure section and See a a The pneumatic which measures section, air 4-5. compressor and Py identified flow, Px output provides two as pressures valve these pressures to the main metering are applied governor bellows. Thus these regulated bellows and acceleration presfunction acting valve bellows, on the metering as the sures, valve Through metering of system. servo a system regulated valves, and flapper Px and Py the to pressures are metered fuel schedule. In provide See Figure 4-6. the desired valves, four orifices flapper and schematic this simplified we see and one Px flapper. These flapper valves three Py flappers are closed and are opened by the flyweight at a initially governors predetermined flapper engine RPM. The derichment and enrichRPM's flapper and alter ment the acceleration open at intermediate fuel schedule These the engine surge zone. to bypass two funccalibrated flow bench and are not field adjustable. tions are on the The set points of the RPM overspeed and RPM underspeed flappers field The RPM overspeed adjustable. is adjusted are to provide an overspeed controlled engine RPM of 103. 5% to 104% RPM. governor The RPM underspeed flapper is adjusted to ground idle low RPM idle high RPM. and ground -

-

"orifices"

4-10

Principles

of Operation

of operation is that Px or Py pressure varies The principle as valve orifice function flapper nozzle. relative of position the to a from a ground idle steady condition, For example, state the RPM underspeed flapper is slightly unseated and the Px-Py valve differential has positioned the main metering pressure If we advance lever for ground idle fuel flow. the condition to high RPM, force spring the the speed cam rise increases on and drives flapper it closer Py pressure increases to the nozzle, relative differential force the to Px and the increased on goverstrokes valve further the metering nor bellows open to increase fuel flow and RPM increases As the RPM to the high selection. flyweight forces increases, increase the underspeed governor valve to unseat release and will cause the flapper some Py to steady condition higher and state at the pressure resume sea valve position 1ected RPM. Thus the flapper is determined by flyweight forces against of force balance imbalance the governor or speeder spring forces. governor lever If the power is now advanced from flight idle, the main leaf valve cam rise applied underspeed metering to the governor valve spring, flapper Py again and seat the toward the moves stroking additional increases, valve open to supply the metering fuel scheduling fuel flow. leaf spring force By integrating the force, with the underspeed speeder have, in spring we governor effect, overriden underspeed additional fuel the the governor, flow caused RPM to rise control point to the propeller governor wherein propeller the increa sed engine torque is converted to pitch change action. thrust by propeller governor failed If the propeller to limit RPM or governor in the underspeed occurred Py nozzle, the RPM flapper RPM overspeed point, set then it the to would limit Py pressure increase and the engine 104¶o overspeed 103. 5 RPM. at to governor These

pneumatic

trol unit must

lines be kept

between the inlet sensor free of contamination.

a blockage would increase would unseat to be running on the and

the fuel

con-

4-11/4-12

,

OVERSPEED

O

DISCS T2SENSINGBI-METALLK

DERKH

.................

LO RPM PCDMAX FUEL

T2 SENSOR MS3065

-

POWER

ENRKH

14

Figure Pneumatic

4-6

Section

4-15

Speed

Operation

Lever

-

LOW

RPM Position

is "On the Locks" following the previous Assume that the engine is experiencing a successful start and is accelerating through the 50-55¶o RPM range. Refer to chart. The

propeller

shutdown.

ACCELERAT10N

SCHEDULE 3.6

START SCHEDULE

SURGE ZONE

.......

-

OVERSPEED \/GOVERNOR (MAX POWER)

UNDERSPEED GOVERNOR DROOP LINE WITH SPEED LEVER AT LOW RPM POWER LEVER ATSTART

wf s3

s ( ,¾

4'y

GROUNDIDLE

UNDERSPEED GOVERNOR DROOP LINE wlTH SPEED LEVER AT HIGH RPM POWER LEVER AT START

97.5 100

70

% ENGINE ROTOR SPEED Fuel

Schedule

"On the Locks"

when the Minimum steady state engine speed is requested is position and the speed lever lever in the START power The speed lever is in the LOW RPM position. stop on the adjusted fuel control is so that the USG servo valve starts opening at Point A, reducing fuel flow which slows down the of acceleration until it reaches rate its steady state requirebreak and Point ment at Point B. Point A is called governor GROUND IDLE. B is called The line between these two points droop line. is called the governor

Speed

Lever

Operation

-

HIGH

RPM Position

the speed lever to the HIGH RPM position parincreasing fuel flow and tially closes the USG servo valve, at Point C. This the engine accelerates up to and stabilizes Advancing

of The amount called High Ground Idle. is sometimes only fuel required is normally to provide this acceleration

point

4-16

Speed

Lever

Operation

-

HIGH

RPM

Position

(Continued)

slightly Governor than the steady state requirement. more break place intersection, fuel flow at decreases takes that and the rate of acceleration slows down until Point C is reached. Point B and Point A line is often drawn between C to illustrate Load Line. the "On the Locks" ACCELERATION SCHEDULE

SURGE ZONE

3.6--

OVERSPEED GOVERNOR (MAX.POWER)

Wf/Ps3 INTERMEDIATE UNDERSPEED GOVERNOR DROOP LINE WITH SPEED LEVER AT HIGH RPM.

POWER

Y

POWER LEVER AT FLIGHT IDLE 7'O

O

LEVER

POSITIONS

100

% ENGINE ROTOR SPEED Fuel

Schedule,

Propeller

Governing

of the fuel control operaFLIGHT IDLE and position between Lever The line drawn through Point X and Point Y repreMAX. The working extremities rate. sents the power leaf spring of this line are where it intersects the USG line and the OSG line. Here is how the name Underspeed Governor was deFLIGHT IDLE rived. The Power Lever rise is holding at cam the USG servo valve off of null towards its closed condition. In other words, not fuel the engine is being prop governed, control malfunctions (USG) governed. If the prop governor direction, in the underspeed the USG will eventually take over fuel flow to keep the engine rotor and increase speed up. malfunctions if the prop governor in the overConversely, speed direction, take over and decrease the OSG will eventually fuel flow to prevent overspeed. destructive

Refer to Chart tion for Power

for an illustration

4-17

Power

Operation

Lever

-

FLIGHT

IDLE

to MAX

of the Power Lever from FLIGHT IDLE toAn advance MAX merely wards "walks" the control output up the 100% speed line. The Power Lever cam rise continues increase, spring and further closing loading the leaf to valve. fuel combustion Again, increased the USG servo is converted to higher torque or power. energy Eventually fuel flow by increasing the increased lever equals rise maximum allowed by the the power cam acceleration schedule. This condition Max at Power occurs (Takeoff). Further closing of the USG servo valve is ineffective.

"requested"

.XXg ACCELERATION

SURGE

SCHEDULE

POWER LEVER AT MAX ,

ZONE

3.6 OVERSPEED GOVERNOR (MAX.

POWER)

LEVER AT INTEERMEDIADGEPOERENROR POWER

INTERMEDIATE POWER UNDERSPEED GOVERNOR DROOP LINE WITH SPEED LEVER AT CRUISE (96°)

| | 70 ENGINE ROTOR SPEED

°/o

Fuel

Cruise

Power

Schedule,

Cruise

96

100

Operation

Operation

actually cruise RPM, can be bet ween 96% and power, 100%. simultaneously Retarding speed lever resets the the This is underspeed and the prop governor. accomgovernor connecting plished by linkage the fuel control to the prop govwould operation is also retarded, If the power lever ernor. 100%. If the setting lever mid at be identical to some power ' walk" back along fuel flow will retarded, lever is not power partially will schedule. The enrichment valve maximum the fuel flow so as not to encounter close to lower the surge zone.

Cruise

at many While operation intermediate is possible, by

4-18

the engine

manufacturer.

speed power

lever

and

(speed)

power settings

lever positions must be approved

ACCELERATION

SCHEDULE

SURGE ONE MAX

DNDERSLIENEEDW

s3

LEVER

THESRNEOERD

REVERSE

MIN REVERSE

AT CRUISE (96%) BETA MODE SPEED BY CONTROLLED UNDERSPEED GOVERNOR

I O

96

70

O

100

%ENGINE ROTOR SPEED Fuel

Schedule,

Pitch

Reverse

Reverse

Pitch

Operation

Operation

mode

of operation, the propeller no longer governor into reverse posiMoving the power lever control which in turn changes the propeller blade angle. does not contact The power lever cam the undermode speed governor beta leaf spring during of operation. the and causes Reverse pitch loads the propeller the engine to try and go underspeed. results in The tendency to go underspeed close and flow increase fuel the USG servo valve starting to to maintain If full reverse pitch is selected, fuel flow s eed. will line in its attempt up the underspeed to governor maintain After schedule. speed until it reaches the maximum be avoided. This extreme speed loss cannot this intersection, and even then for only short condition encountered is seldom durations. In this

governs RPM. tions, the pitch

"walk'

Beta

Mode

Operation

Operation below the FLIGHT with the power lever IDLE position is referred Propeller pitch control to as Beta Mode operation. controlled This is manually in this range. by the power lever is in contrast IDLE and above wheree at FLIGHT to operation automatically propeller pitch is maintained by the prop governor. Beta Mode operation during is encountered ground handling (Taxiing) After the engine has been and reverse pitch braking. "On the Locks" and checked and started out with the propeller momentarily it is desired aircraft, lever is the power to taxi the Propeller pulled back towards REVERSE the blades. to unlock pitch is now controlled by the power lever.

4-19

0 L\D

o

POWER MOP

SYNC

FLT IDLE LATCH ARM

ON

R.P.M. OFAU

E

0 EV

THRUST

\

LEVERS

ENG

CONDITION

STOP

EMERGENCY

0

FEATHER

\

FRICTION

LOCKS

Engine

Control

Quadrant

LEVERS

ENGINE

CONTROLS

levers of the Two cockpit the operation are used to control engint: lever. The power the power lever and the condition lever is marked quadrant with the following positions: The Reverse, Ground Idle, Flight Idle and Maximum. condition lever quadrant is marked with the following posilevers Low RPM and High RPM. The power Feather, tions: integral and the condition incorporate flight idle latches, latch" levers between low RPM and Feather. have a

"gate

Engine

Speed

Control

The condition lever is interconnected underto the fuel control (P.Gov.) speed governor and propeller (USG) the governor when operated between the low RPM and high RPM stops on quadrant. the High

RPM Low RPM

Lever

ondition uadrant When it will unseat

Propellor

Underspeed Governor

3overnor

the condition

lever in the feather position, is placed close the engine valve, fuel shutoff then propeller feather valve.

manually

the

High RPM

Fuel

Low R

3hutof

f' \/alve

Feather Condition

Quadrant

Lever Feather

Valve

4-21

Engine

Control

Power

lever The engine interconnects power control and fuel control servo power units have rig pin holes (.125" Dia.) degree gree angle and flight idle -40

Forward

Flt

to the propeller lever quadrant. at full reverse angle.

-0

pitch These de-

Thrust

Idle

Thrust Power

Propellor Pitch control

Lever

Fuel

Quadrant The power lever sets fuel schedules, and through a propeller low pitch stop. pitch control, sets the propeller lever selects The condition engine RPM. Engine RPM may by the propeller be controlled underspeed governor, goverThe controlling is a nor or overspeed governor. governor function of mode of operation or condition. must performance For optimum and handling, the controls maintenance manual specifications. be rigged and trimmed to propeller pitch setting RPM limits, Rigging involves governor (Beta tube adjustment), propeller pitch control to propeller underspeed valve (fuel control), control to main metering and the quadrant levers to propeller to governor governor, NOTE: There engine controls. are three separate controls. adjustments at each end of the push-pull

"push-pull"

making Trimming those permissable the fuel control means for optimum fuel schedules adjustments will provide that the fuel flight idle and cruise, engine maximum start, power, density. adjustments in a specific These are accomplished fuel density setting, is which (1) (2) start fuel flow, sequence, pressure", flight and idle fuel flow. (4) (3) max power or accordance These should be accomplished in strict adjustments with maintenance manual procedures.

"head

4-22

Valve

Lot

og/

/we

4-23

The following for making is a typical procedure (Observe speed checks: Flight Manual procedures engines). starting P/L

Condition 1.

Engine

2.

3.

-

C/L

Data

engine for

Tolerance

Required

F. I.

Low

Time from rise in ITT to 70% RPM.

60 Sec. Max. and within ITT limit.

O. S. G. check

Max.

High

Prop RPM

103. 5%

Unlock

Slight

High

start

prop.

on the locks check.

104%

-

Rev. 4.

U. S. G. Min.

G. I.

Low

Engine RPM: Revload 10 PPH inc. from Min. ITT.

69%

5.

U. S. G. High

G. I.

High

Engine RPM: Revload 10 PPH inc. ITT. from Min.

96%

NOTE:

Oil

be 66oC

to 80oC for prop

gov.

97%

-

RPM

checks.

6.

Prop

Gov.

High

500SHP

High

Engine

RPM

99. 5%

7.

Prop

Gov.

Low

500SHP

High

Engine RPM: Reduce C/L setting until no further drop in RPM

93. 5%

NOTE:

8.

Cruise separation.

4-24

temp must

71%

-

power

For Step 7, the tolerance listed C/L mid-travel before reaching 500SHP

96%

ITT inc.

-

100. 5% 94. 5%

should be obtained position.

P/L to Min. plus 10 PPH WF toward reverse.

Reduce

-

92%

-

93%

ENGINE The

OPERATION

in three different modes: engine may be operated mode; (2) Flight idle; and (3) Flight mode.

(1)

Ground

referred sometimes is selected to as Beta from full reverse by placing the power lever at any position to The fuel flight idle. Figure 4-7. See Beta Mode Schematic, operation supply engine is not sufficient on the proto support peller oil propeller reduces so pressure governor governor angle to the minimum angle selected propeller blade by the propeller pitch control. At this time the Beta Mode light will pitch angle is now selected indicating by illuminate the propeller This mode is used for ground taxi, in either the pitch control. manipulates forward direction. When the operator or reverse the power lever either forward or aft of ground idle propeller by the pitch control blade angle will be changed and the fuel control underspeed sensing load change the on the governor will modulate engine chamber the fuel supply to the combustion condiselected RPM required maintain by engine the that to to 97% RPM. lever, within of of 70 the tion range to mode

Ground

-

-

setting designed specifically for the airFlight Idle is a power landing characteristic and is the minimum in flight power frame Flight Idle incorporates propeller pitch setting. a selected angle (13. 5 degrees) fuel flow. and a predetermined At this should symmetrical setting produce the engines thrust power sink and provide desired rate. a speed is controlled by the propeller Mode or when engine flight lever is advanced beyond when the power occurs governor idle range, and the condition lever is at high RPM or within 96% to 100% RPM. 4-8). cruise (See Figure range Flight

-

Additional

fuel

the propeller tions as a fuel by

governor.

Engine

RPM In

to increase to that selected this mode the power lever func-

and the propeller modulates governor by the the torque power produced to absorb produced this power to propeller thrust.

throttle

propeller blade angle engine and converts

ANTI-ICING

engine

causes

SYSTEM

bleed

air is directed from the turbine plenum through valve solenoid manifold. From to the anti-icing shell the hot bleed air is directed to the anti-icing inlet duct. (which warms the engine inlet duct) and to the nacelle valve The anti-icing solenoid and its associated plumbing are located left side of the engine. is A micro-switch on the lower valve installed in the anti-icing solenoid to provide a cockpit indication when the system is turned on.

the anti-icing the manifold

4-25

1

GEAR PUMP

INOP./BETA

FROM LUBE TANK OIL

VENT CASE

DUMP CASE

TO

LUBE OIL PRESSURE

y

CAM SET

's,

TORQUE R SENS

MIN SPEED ST°"

RESET PISTON

E---ma--mma V#7

,,.

# Æ##

,

..

RANGE NTS REGULATOR 100±5PSIG

UNFEATHERING PUMP

TO

CHECK VALVE

..

Y

7

,

Ma

errv/ CHECK

A

PROPELL GOVERNO

'

IN--a

RELIEF

VALVE

_350

a-

VALVE PSID e-

MAX SPEED STOP

am as am um

CONTROL SPEED LEVER COORDINATED SETTING WITH SPEED SHAFT LEVER ----A em ma

SF PEE 7A

5 VENT CASE

NTS PRESSURE SWITCH NTS

MANUAL PROP FEATHER

TO

L

CKOUT NT (NC) SOLENOID

BETA LIGHT

LVE G VALVE

FEATH VE

OSELOC CH

V

OE

E

SWITCH

CAM

PROPELLER

PROPELLER PROPELLER

OIL

FEATHER

BETA)

PITCH

TUBE

CONTROL

DIRECTION

D

H-#-(+)

CASE

a------

....

...""

c

i

Emissa-same--

FIGURE

7-2

BETA

MODE

TO FUEL CONTROL MANUAL FUEL VALVE

POWER LEVER CONNECTION

e- um mmmmammaamm a- eGEAR CHECK PUMP VALVE VENT

DUMP CASE

TO

1NOP./BETA RANGE NTS REGULATOR 100*5PSIG

FROM LUBE OIL TANK

UNFEATHERING

NTS

BETA

M1N SPEED= STOP

//////

//

o

••

IN

p

-

/

"-

...

CH CK vALVE

PROPELLER GOVERNOR

.

.

MAX SPEED STOP

A

.

/

RELIEF

VALVE

CONTROL SPEED LEVER COORDINATED SETTING WITH SPEED

5

75L

HAELR

O

RES

WS

----

um em

///

LUBE OIL PRESSURE

TORQUE SENS R

PUMP

Ÿ/////

TO

ammmmmmmm RESET PISTON

L

saname

NTS CHECKOUT (NC) SOLENOID

LIGHT a

.a

CHECK VALVE

L

I

J

y

+

L L _a

BETA PRESSURE SWITCH

CHECK

FEATHERI

---7

a

um

...

J

G VALVE

NTS LOCKOUT VALVE ABOVE 35° CLOSED

y

VALVE

--------mus

/

mm CAM

PROPELLER

" PRO

IL

E

(BETA)

OPELCLEORTROL

BE

L \

TO ',

CASE be

==--

mim

TO FUEL CONTROL MANUAL FUEL VALVE

ww.mi

i i

a-ass PROP

GOVERNING

MODE

-

ENGINE

ON

SPEED

POWER LEVER CONNECTION

ANTI-ICING An oil-to-fuel system icing.

and

SYSTEM heat provides

(Continued)

is incorporated exchanger controlled automatically

into the fuel fuel-filter anti-

is taken of heat transferred Advantage to the fuel by the oil-tofuel-filter for anti-icing. Heated fuel heat exchanger providing fuel is supplied unit from the exchanger disto the fuel control Internal in unit and charge side. porting in the the fuel-control high-pressure directs the heated fuel to a thermopump assembly externally unit. The static valve located to the fuel control partially valve all fuel flows is at thermostatic open during and permits mixing of the hot, heatwhich fuel icing can occur fuel with inlet fuel to the boost pump. exchanger discharge of the fuel filter. The fuel mixing upstream occurs

SENSING

TORQUE

SYSTEM

(See Figure

4-9)

by the turbines developed by the engine is recovered The power reduction and transmitted gearing to the output through the shaft. A torsion shaft is used to couple the turbine to the reof duction The torsion shaft resembles gearing. a section 5/8 inches long. about inch in diameter and 24 As loads tubing applied shaft the torsion to the engine, twists a predictable are By measuring amount. this twist, the torque (power) being developed by the engine The torque (twist) may be measured. of forward installed measuring device portion in the lower is reduction capable of measuring both housing and is the gear positive If a negative and negative torque conditions. torque is sensed, measuring device develops the torque an oil pressignal posi·that moves the propeller toward the feather sure loads, if Note: excessive, Negative tion. torque cause very loads to be applied If a positive severe to the airframe. torque device is sensed, develops the torque measuring an oil presin the cockread on an instrument that is ultimately sure signal pit as shaft horsepower. The engine Therefore, unit matched

is matched transducer torque sensing if this unit should require replacement, to the engine will have to be obtained

AiResearch

Manufacturing

A negative

torque pressure

a calibrated from

Company.

switch, light NTS indicator equipment. An NTS operational are standard prior with engine The start. to or concurrent must be operating satisfactory prior to flight.

test switch is made system

to the engine.

and check

NTS

The NTS system is rendered inoperative when the power lever setting is reduced below flight idle. This feature is provided by incorporating torque oil dump valve into the proa negative peller In addition pitch controller. to this, the propeller

4-28

TORQUE

SENSING

(Continued)

SYSTEM

RPM reset with an oil pressure operated is equipped governor oil dumped, When negative is the proppressure torque servo. 4-9). is reset (See Figure to 105% RPM. governor involves checkout of the NTS system check and NTS oil check valve test. functional check procedures are:

A complete

1.

Power

2.

Battery

lever switch

Place

3.

in flight

engine

idle

a rigging The rigging

check,

setting.

on. control switch at "AIR START", observe NTS test light "ON".

engage

NTS test switch,

observe Slowly move power lever toward ground idle, The NTS light must not extinguish NTS test light.

4.

lever until the power reaching and prior to

Slowly

5.

light

just behind

ground

flight

idle

stop,

idle.

lever The NTS move the power to flight idle. before reaching flight idle must stop. come on

See Airframe

test

is

Flight

Manual

for

functional

check

and

check

valve

procedures.

ENGINE Engine stage

INSTRUMENTS exhaust

gas temperature

turbine nozzle turbine temperature"

The system compensator Manual for

vanes, (ITT).

is measured

in

thus it will be referred

incorporates a thermocouple and gauge unit. See Section engine ITT limits.

the second to as "Inter-

harness, engine ITT I of Airframe Flight

instrument The horsepower is a voltmeter movement type involts or power off the instrument strument, and at zero should indicate 700 horsepower. If not, it can be calibrated 700 to horsepower with a calibration screw on the front of the instruThe instrument receives developed by ment. a D. C. voltage Thus the HP instrument is D. C. system the torque transducer. powered. fuel pressure, The engine oil pressure and gauge unit provides oil temperature information. This is a D. C. powered system, consisting of a gauge unit, oil pressure fuel prestransducer, bulb. and a temperature sure transducer

4-29

FLOW SENSOR-TURBINE

TRANSMITTER

FLOW SENSOR-TURBINE

TRANSMITTER

LJ

LJ

SIGNAL CONDITIONING UNIT

FUEL FLOW RATE INDICATOR

4-30

FUEL CONSUMED INDICATOR-TOTALIZER

FUEL FLOW RATE INDICATOR

ENGINE

INSTRUMENTS

(Continued)

The engine RPM gauge is a vernier movement °7o in of RPM, and is powered by a standard meter generator.

instrument

jet engine

scaled

tacho-

provides The fuel flow measuring system an accurate of the fuel flow rate to each engine and the total measurement of a flow fuel consumed The system consists by both engines. conditioner, (transducer) for each engine, sensor a signal a flow rate indicator and a fuel consumed for each engine totalizer. The fuel flowing (turbine transthrough the fuel flow sensors ducer) pulses is converted at a rate that is proto electrical These portional to the volume of fuel flowing to each engine. for conunit, pulses to the signal conditioning are transmitted which drive ditioning and conversion the flow to analog signals The signal conditioning unit through separate rate indicators. channels drives the fuel consumed totalizer.

PROPELLERS The propellers used on the Model 690 Turbo Commander are HC-B3TN-5L/LT10282 full Hartzell speed, H+4 constant feather, 3 blade, capability. The 106 inch diameter reversing propeller has 14. 24 inches and prop tip ground clearance, clearance. 14. 5 inches The propeller is tip to fuselage with bulkhead. The prospinner equipped and spinner a metal peller mounted is flange to the engine output shaft., and rotates when counterclockwise from behind viewed the nac elle. spider The propeller is a one piece unit to which the aluminum blades and indexed by two piece blade clamps, are attached incorporating counterweights, lock and start thrust bearings plates. The blade bearings through grease gun are lubricated zerk fittings. See Figure No. 4-10. forces The pitch change toward high pitch and feather are defrom blade springs counterweights and feathering rived operating against the pitch change piston of the propelle r. Propeller control oil pressure is used to move the blades togovernor ward low pitch and reverse. 4-11. See Figure The propeller by either is controlled the propeller governor pitch control mechanism, depending or the propeller on the operation. When the propeller mode of engine is controlled by the propeller its operation is similar to that on governor, The propeller engine. either allows a reciprocating governor oil to be sent to the propeller (less pitch) or drain from the propeller engine the selected (higher pitch) in order to maintain speed.

4-31

PROPELLERS

(Continued)

by the propeller pitch is being controlled different. unit, its operation is somewhat A long tube (Beta tube) is attached to the front end of the propeller aft through the hollow and extends engine piston output shaft. of The aft end of the Beta Tube contains around ports a group its circumference that mate with a corresponding group of Power propeller pitch control unit. ports When the the on "Reverse" between position and Lever is moved to some "Flight Idle" the propeller will assume pitch control a defiThis places nite position. the ports in such a position that be allowed oil will either to go to the propeller or drain from of illustration, it. For purposes that the Power assume "Reverse" from Lever is moved to "Ground Idle". When control

the propeller

Oil is allowed

to drain from the propeller (a higher pitch is and the propeller piston aft, as the piston moves aft so does the Beta tube. When the propeller moves moves corresponding to the position to a "Ground Idle" blade angle pitch control and on the Beta tube the ports in the propeller will be covered further pitch change. The up thereby stopping until a different blades will now stay in this position Power setting is made. Lever selected)

"Reverse" Power setting between Lever In this manner every "Flight Idle" will result in a predetermined blade angle. and It is extremely important adthat the Beta tube be properly The Beta tube is adjusted by screwing it in or out, justed. being from the forward end of the propeller dome. access service manuals for exact rigging and Consult the applicable procedures. propeller maintenance PROPELLER

SYNCHRONIZATION

SYSTEM

is comprised of a transThe propeller system synchronization istorized synchronization actuator, control box, a speed setting pickups and slave governor with trimmer. Magnetic a master electric pulses in each propeller supply synchthe to governor ronizer box. control will in these pulse rates Any difference lobox to actuate the speed setting actuator the control cause cated on the slave The speed setting actuator, (right) engine. which is connected by a flexdrive shaft to the slave governor rod end fitting and special the governor (trimmer) resets assembly, by the exact synchronize needed amount the to precisely slave engine with the master Propeller (left) engine. governor control and operation remains normal except that; once the pro+ 25 RPM pellers synchronized within are manually (propeller synchronizing speed) and prop sync switch is turned on, match system will automatically the RPM of the slave engine with the master This limited feature engine. prevents range the slave engine from losing more than a fixed amount of RPM in case the master while the prop sync engine is feathered system is turned on. ¯he

4-32

SPINNER

SAFETY FLEXLOCK

BOLT

NUT O-RING OIL TRANSFER (BETA TUBE)

FEATHERING

TUBE

SPRINGS PISTON O-RING REVERSE PITCH STOP TUBE

DUST SEAL BLADE BEARING

o

COUNTERWEIGHT AUTO HIGH PITCH STOP UNITS

OIL SEAL

MOUNT BOLT PROPELLER

SHAFT

FLANGE HARTZELL

PROPELLER

HC-B3TN-5FL/LT

Figure

10282

H

+

4

4-10

4-35

I

mm

VENT CASE FROM LUBE OIL TANK

f

DUMP TO CASE

TO

LUBE OIL PRESSURE

NTS REGULATOR 10015PSIG

------

-------

mm

GEAR PUMP

CHECK VALVE

CAM SET IR7E

TORQUE SENS R

PROPELLE GOVERNOR

-4

-

IN

CH CK VALVE

.)

MIN SPEED STOP

,

,,

ED UNFEATHERING PUMP

a mm

RESET PISTON

RELIEF

NATED SETTING WITH SPEED LEVER SHAFT summmesmaså mm um

VAL E

PSID 300-350 em um em--

SF PE

a -a

LSPEEDCOOND

-

em

5 NTS

VENT CASE

PRESSURE

MANUAL

TO

HER NTS

L

BETA

LI

EC

E

L

CK

H

BETA PRESSURE SWITCH

CHECK

CLOSED

VALVE

BEEG

ALVE

35

CAM

PROPELLER

PROPELLER CONTROL PITCH CT

E

TO FUEL CONTROL MANUAL FUEL VALVE

POWER LEVER CONNECTION PROP

GOVERNING

MODE

-

ENGINE

SPEED

LOW

PROPELLER

SYNCHRONIZATION

SYSTEM

(Continued)

The prop sync system is to be turned off during take-off and landing. slightly After take-off prop RPM should be decreased manually off stop) high cruise RPM the range (back to synchronized and the prop sync switch turned on. See Airframe maintenance Maintenance for preventative Manual and adjustments of this system.

4-37

EREA

PROPELLOR PITCH CONTROL ARM

/

i

COMPRESSOR (REFERENCE)

CASE

PROPELLOR FEATHERING VALVE

ITT COMPENSATOR

690/690A ENGINE CONTROL LINKAGE INSTALLATION

/ '

"

y

4-38

ENGINE FUEL SHUTOFF VALVE

L FUEL-HYD N

G

AUXILIARY HYDRAULIC PUMP HYDRAULIC RESERVOIR

FLEL

PRESSURE WITCH

HYD

DRIVEN

ENG

EYDD U

o

VSHUTOFF

SHUTOFF VALVE

VALVE

ACCUMULATOR-REGULATOR PRESSURE GAGE FLAPS UP LANDING GEAR UP

1

FLAP CYLINDER

LANDItsG G AR WING VAl VE I LAI' COtTHOL

LAfsDING GEAR

S

er

y

PRIORITY VALVE

I I LEFT MAIN GEAR UPLOCK CYLINDER PRIORITY VALVE

WHEEL DOORS CONTROL VA E

,,,,,

a-tr.rry

rr

AIRPRESSURE

PARKING BRAKE VALVE

EMERGENCY AIR STORAGE CYLINDER

ACTUATING

FROM PARKING BRAKE VALVE RRE

SUPPLY

I

TO WHEEL BRAKES

TN ACYNLEAR

-LEGEND-

i

so-77,,

-RIGHT MAIN GEAR UPLOCK CYLINDER

WELL DOORS UA G CYLINDERS

CJI

.

METERING VALVES

-

WHEEL

POWER BRAKE VALVES

w/77477,wwy,

wy, WHEEL WELL DOORS ACTUATING CYLINDERS

R LIEF VALVE (1250 LBS)

W1NG FLAP FLA

RETURN

OWCONTROL

NOSE GEAR CYLINDER

CHECKVALVE

NOSE GEAR STEERING CYLINDER ----

MECHA

OCNAL

T

L

SYSTEM PRESSURE

GEAR UP POSITION

AUXILIARY PRESSURE

RETURN

/

GEAR UP

GEAR UPLOCK

GEAR DOWN

FLAP

UP

FLAP DOWN

PSRESSSEU E

AUXILIARY

RETURN

PRESSURE



4

N

GEAR DOWN POSITION GEAR UP

PWÆiWJ FWES'S -

-

-

SYSTEM

GEAR UPLOCK

GEAR DOWN

FLAP UP POSITION

FLAP

FLAP DOWN POSITION

FLAP DOWN

UP

PRESSURE

RETURN -

MECHANICAL

ACTUATION 23 16

Landing

5-2

Gear-Wing

Flap Control

Valve

Schematic

SECTION HYDRAULIC

5 SYSTEM

INTRODUCTION hydraulic hydraulic provides system for operapressure landing flaps, wheel and of wing steering, tion the nose gear, inbrake system systems. Major hydraulic components are nacelle stalled and consist of a hydraulic in the left engine fluid reservoir, shutoff accumulator-regulator valves, and auxiliary hydraulic and switch. system A the pump pressure hydraulic located in system center inthe pressure gauge, panel and connected into the pressure system, strument in psi. hydraulic registers During normal system pressure installed operation, engine driven hydraulic pumps, on the housing of each engine section supply system accessory upper Hydraulic fluid flows from the reservoir through pressure. shutoff valves electrically operated to the engine-driven valves, located in the supply hydraulic The shut-off pumps. provided off the flow line to each hydraulic shut to pump, are in of an of hydraulic fluid to an engine-driven event the pump hydraulic fire and to facilitate maintenance engine on the installed downstream from The accumulator-regulator, system. 900-1075 hydraulic maintains of the a system pressure pumps, pulsations caused by intermittent psi and absorbs pressure fluid flow from the engine-driven hydraulic A prespumps. valve, installed in line at the bottom relief the fluid return sure of the hydraulic reservoir protects the system from overpressure caused by thermal expansion. In the event of normal hydraulic failure, auxiliary hydraulic available is system system the to brakes. brakes, and parking operate the wing flaps, nose steering auxiliary which is supplied hyThe electrically-driven pump, of fluid contained.in draulic fluid from an emergency source produces of 500-570 the bottom of the reservoir, a pressure 30) psi auxiliary operate system. the (+ to The

Hydraulic cylinders actuate the nose and main landing gear, main uplock mechanisms and wing flaps. The cylinders are controlled landing through a (dual-functioning) gear wing flap valve, control mechanically linked to landing gear and wing flap control leverso check valve incorporated in the landing A gearcylinders of wing flap control valve, retains fluid in the uplock when main is retracted. In it event landing of presthe the gear fluid retained the hydraulic system, sure loss in the hydraulic cylinders will prevent in the uplock the main gear from extending until the landing control placed lever is in the down position, gear fluid from the uplock cylinders. releasing The nose landing gear is retained by hydraulic from the in the up position pressure

5-3

INTRODUCTION normal landing locked

(Continued)

If normal is lost the nose system pressure position free-fall and be to the extended down" by action of the nose gear bungee spring. Nose actuating is accomplished wheel steering through a hydraulic A bypass valve installed cylinder attached to the nose gear. in the hydraulic steering system prevents the nose wheel The wheel brakes from being turned when it is retracted. and nose wheel steering through power brake are controlled valves, which are linked pedals. Power to the rudder-brake brake valves by applying pressure to the upper are actuated pedals. portion of the rudder-brake

system. gear will

An air storage bottle containing compressed nitrogen is loand connected cated in the baggage compartment to the main landing actuating cylinders by gear hydraulic-pneumatic nitrogen is utilized Compressed tubing and hoses. to assist in lowering system the hydraulic the main gear during normal and provides needed for emergency the pressure gear operation extension of the main gear in the event of hydraulic system

failure.

RESERVOIR nacelle hydraulic reservoir, installed in the left engine of fluid and inwell, is serviced with 3. 2 U. S. quarts Hycorporates a fluid expansion space equal to 1.06 quarts. draulic installed in the fluid flows through a replaceable filter, of the reservoir bottom into each of the main supply standpipe outlets and on to the engine-driven In the event of a pumps. hydraulic leak in the normal supply of fluid system, a reserve below the reservoir contained flows out through the standpipe outlet hydraulic system emergency to supply fluid to the auxiliary Hydraulic fluid is returned through a pump. to the reservoir The reservoir fluid foaming. port, to decrease tangential return is vented overboard in the reservoir through a vent line installed of the reservoir. A drain plug is located in the bottom cover. Access filler cap is gained through an access to the reservoir located nacelle service door, left engine surface, on the upper "Red" hydraulic with MIL-H-5606, fluid. The

wheel

The hydraulic located in the bottom of the hysystem filter, draulic is held in place by a spring-loaded plate. reservoir To filter, reduce hydraulic system the remove to zero, pressure reservoir retaining bolt and cover, and lift filter remove cover Filters from the reservoir. at should be cleaned or replaced inspection prescribed in the aircraft intervals guide.

5-4

SHUTOFF

VALVES

hydraulic fluid supply line to each engine is connected shutoff attached valve to a to the bottom of the hydraulic fluid reservoir. Each valve is actuated by a reversible d. c. electric which automatically motor, stops the valve gate when it is driven Each to the fully open or closed position. and protected shutoff valve is actuated switch by a guarded breaker, by a 5-amp circuit located push-to-reset on the edge of the trim tab control forward panel. Under normal shutoff valve remain conditions, in the operating switches OPEN position and are protected by a switch guard to preeach switch closing. The guard covering vent accidental is secured with a which is easily safety wire, The hydraulic broken to open the guard and close the switch. make it possible and switch circuit shutoff valves to stop the in the event fluid to the appropriate flow of hydraulic engine of emergency. Hydraulic also facilitate mainshutoff valves of hydraulic by of providing system the tenance a means fluid flow at the reservoir. stopping hydraulic The

"break-away"

ENGINE-DRIVEN

HYDRAULIC

PUMP

hydraulic engine-driven positive-displacement, A gear-type, installed drive In the engine is pad. accessory on an pump becomes inoperative, remaining event one hydraulic the pump of supplying sufficient fluid flow and pressure pump is capable in Check valves installed system. the hydraulic to operate hydraulic and accumulatorlines between supply the pumps the regulator, fluid prevent an operative pump from discharging inoperative through an pump.

ACCUMULATOR-REGULATOR accumulator-regulator is installed The hydraulic in the left nacelle wheel-well, and consists of a hydraulic engine presvalve, unloader valve, relief valve, pressure sure adjusting and accumulator The hydraulic adjusting piston. pressure valve controls unloader valve, -which regulates hydraulic the received from hydraulic engine-driven the pressure pumps. The unloader valve is adjusted hydraulic system to maintain between 900 psi (minimum) and 1050 (+ 25, psi. pressure When system 1050 exceeds unloader allows psi the pressure the system and return to bypass to the reserpump pressure voir. When system is decreased to 900 psi, the unpressure loader valve permits to be applied to the system. pump pressure The hydraulic relief valve is adjusted fluid to return pressure hydraulic when reservoir 1300 exceeds system to the pressure This protects hydraulic of unloader psi. event in system the the valve malfunction. The piston type accumulator, which is 600 charged with nitrogen psi provides to an air cushion gas, which absorbs for the hydraulic pulsating system the pressure -0)

5-5

(Continued)

ACCUMULATOR-REGULATOR

and operation of hydraulic from regulator modulation regulating in Malfunctions system components. the pressure by usually caused accumulator-regulator of functions the are be of operation and indicative hyvalve faulty poppet may draulic fluid contamination to clean the hydraulic or failure intervals. filter at required resulting

LANDING

GEAR AND FLAP

SELECTOR

VALVE

valve is located The landing on the gear and flap selector floor below control pedestal. immediately engine cabin the of three basic components: The valve consists (1) The valve floor); The assembly above cabin seal plate the (2) (located

(mounted on the cabin floor skin); (located below the cabin floor).

of the system plumbing most and out of the cabin and the when necessary. servicing

assembly (3) the manifold By using a valve of this type, below the floor may be routed accessible for valve is readily

of the assembly consists of steel The actual valve portion nylon seats. A check valve is inplates that bear against of the valve stalled between the landing gear and flap portions from entering system pressure the the emergency to prevent landing gear system. FLAP

SYSTEM

from the flap selector valve through flow control cylinder located to a single flap actuating on the left valves side of the aft fuselage. The flow control are installed in such a manner the return that they are at times restricting cylinder. This allows flow of fluid from the actuating the flaps of whether slow rate regardless they are to travel at a uniform being extended aircraft During cruise when the or retracted. or is parked, is left in the up position exposing the selector one side of the actuating cylinder at all times. to hydraulic pressure

Fluid

flows

valves

If the aircraft for an extended is parked of time, it is period for the flaps to extend normal drops. as the system pressure because This occurs the mass or weight of the flaps is concentrated behind the hinge line.

LANDING The nose

GEAR

SYSTEM

cylinder to extend, a single actuating gear utilizes and lock the nose wheel. retract, To assist in extending the should loss is bungee spring nose wheel pressure occur, a a provided. The spring bungee also helps lock the nose wheel in the down position.

5-6

III 4

lill

\

12

12

h 10

11 UNLOADED

1.

2. 3. 4. 5.

6.

CONDITION

LOADING

ENGINE-DRIVEN HYDRAULIC PUMP PRESSURE SYSTEM PRESSURE VALVE POPPET REGULATED PRESSURE TO SYSTEM (RETURN) PUMP PRESSURE TO RESERVOIR HYDRAULIC PRESSURE RELIEF VALVE UNLOADER VALVE

Hydraulic

10

11

Pressure

7.

8. 9. 10. 11. 12.

CONDITION

HYDRAULIC PRESSURE ADJUSTING VALVE (UNLOADED ADJUSTING) UNLOADER BLEED (RETURN) ACCUMULATOR PISTON AIR PRESSURE VALVE AIR FILLER SCREEN

Regulator

Unit

Schematic

5-7

1

2

26 18

1. 2.

3. 4. 5. 6. 7. 8. 9.

2521

10. 11. 12. 13. 14. 15. 16. 17. 18. 19.

24

20. 21. 22. 23. 24. 25. 26.

¯'

23

SYSTEM PRESSURE CHECKNUT GUIDE POPPET

OUTLET

SPRING POPPET INLET PUMP PRESSURE RETURN POPPET & SEAT ASSY SPRING GUIDE SPRING (Relief) ADJUSTING CAP (Relief) (Transfer) PLUNGER SPRING (Transfer) ADJUSTING CAP (Unloader) PLUNGER SEAT BALL GUIDE

SPRING (Unloader) CAP ACCUMULATOR PISTON CHECKNUT AIR VALVE PISTON GUIDE RINGS BODY LOCK NUT

22 23 5

Accumulator

5-8

-

Regulator

MAIN

GEAR

cylinders Five actuating on each main gear: (1) are utilized actuating The normal cylinder, The actuating emergency (2) Two aft door actuating cylinder, uplock cylinder, (4) (3) The cylinders. cylinder The normal actuating uses hydraulic pressure operate it to both the up and down positions as determined valve position. by the selector

to

operated cylinder is hydraulically actuating The emergency cycle and nitrogen operated during during a gear retraction is stored cycle. The nitrogen in a cylinder a gear extension The system is periodically in the baggage compartment. serviced through a combination gauge and filler pressure is serThe cylinder assembly located in the left nacelle. viced to 425-525 psi when the landing (maxigear is extended cylinders). The pressure rises in the actuating mum volume 500-700 psi as the landing (the process of gear is retracted retraction decreases causing the volume of the nitrogen the within It could be said then the cylinders to rise). pressure is at all times opposing system that the nitrogen gear retraction There and is aiding are no valves or controls gear extension. associated with the nitrogen system; this makes it unnecessary additional operations in order to perform to extend the gear fail. be over utility system Should the nitrogen should the should fluid of inflated enter this portion the system, the or fully. gear will not retract uplock cylinder is hydraulically moved to the locked operated and hydraulically and spring position to the unlocked installed in line leading check valve is A position. the to one from unlocking uplock cylinder of side preventing the gear the until gear cylinders is selected. The door closing well aft wheel doors. and close the open type The

"down"

"clamshell"

of events that occur when the gear is selected sequence Hydraulic follows. is directed to the up position is as pressure cylinder causing it to retract the nose to the nose gear actuating wheel and compress At the same time, the spring bungee. cylinders is directed to the door actuating to open pressure the aft doors and to each cylinder the on the main gear causing and compress uplock cylinder the spring that to move forward cylinder actuating is installed the emergency on it; causing against When the the air or nitrogen to retract pressure. main gear reaches the wheel well door control the up position, valve is actuated to close the aft doors and uplocks are engaged holding the main gear in the locked position. The

utility system fail, the nose wheel would be pressure regardless by the spring bungee of selector valve The main gear, however, would be held up until the position. safe speed and pilot first slowed the airplane to a minimum

Should

extended

5-9

MAIN

GEAR

(Continued)

At this time the springs on the upgear down. cylinders would unlock the main gear and nitrogen presdown, the wheels sure would extend it, as the gear started would contact the aft doors to open them.

then selected

lock

speed to reduce selecting gear down to reduce main gear as much as possible. It is necessary

BRAKE Power

AND brake

NOSE valves

WHEEL are

to 100 to 105 KIAS before by the the drag encountered

STEERING

installed

on

SYSTEM

the front

side

of

-pilot.

the

immediately in front of the The Sta. 5. 5 bulkhead brake valves in brake meter response to power pressure and have a variable of from output pedal pressure zero to full system pressure. first inch of brake pedal travel causes ports the return deflection close; further pedal in the valves to causes prescylinder and nose steering to the brakes sure to be metered simultaneously. At low output pressures, the nose steering but the brakes is effective, fittings not. Restricted are are cylinder installed in the lines to the nose steering to prevent excessively rapid respons e to hard pedal application. The

between is installed the lines linkage with a mechanical valve and the nose wheel trunion. between As the by-pass valve is moved the by-pass the nose gear retracts, to the byallowing turning off the nose wheel steering, pass position, mechanism, internally contained in the strut, the centering of whether the nose wheel regardless to center or not the brake pedal is depressed. by-pass valve steering cylinder, to the nose steering

A nose

Cam-operated

check

valves

to provide parking brakes. to be trapped in the brake EMERGENCY The emergency electric motor

(3) A Control

HYDRAULIC

are installed When actuated lines.

in

the brake they cause

lines fluid

SYSTEM

hydraulic of: (1) An system is composed driven switch, gear type pump, (2) A pressure relay.

switch turns the electric pressure pump "ON" when the drops when the to 500 psi and turns the pump "OFF" pressure rises The electric to 600 psi. pressure pump will normally cycle (turn "ON" and "OFF") 3 to 5 seconds, providing every The

5-10

HYDRAULIC

EMERGENCY

SYSTEM

(Continued)

for the brakes and flaps only. The operation of pressure switch is the electric pump is automatic any time the master "ON" manipulation requiring pilot. by no turned thereby the Approximately in the hydraulic

WHEELS

one quart reservoir

AND

of fluid supplies

trapped below the standpipe system. the emergency

BRAKES

Conventional split rim type wheels are used with either tube-type gears and are equipped specified The by the owner. tires should as inflated excessive to prevent shimmy.

on all three landing tires or tubeless always properly be and nose wheel

"flat-spotting"

On aircraft

11100 through 11194, three the brakes are Goodyear, accomplished single disc assemblies. Braking is spot, by squeezing the brake disc, keyed to the inner wheel half, between have steel The brake linings the sets of brake linings. caps providing increased life of the linings. The brake service in such a manner housing is constructed that the brake linings changed without airplane may be jacking the the or removing wheel. 11195 and subsequent, the brakes are Goodyear disc type consisting Tri-Metallic Multiple principally of abrake and housing, disc stack, plate. The torque back torque tube, and the back plate with the tube is bolted between the housing disc stack installed on the torque tube.

On aircraft

and should have an operating The brakes are self adjusting measured disc clearance plate and first between pressure for overof 0. 030 inch minimum. from service Remove brake haul when end of any brake return 0. 022 inch or pin recedes with brakes applies. into the spring housing more -

-

STRUTS NOSE

GEAR

STRUT

The nose wheel with MIL-H-5606

is a conventional strut fluid and hydraulic

oleo 100 psi

type strut of nitrogen

serviced or dry

air.

5-11

NOSE

GEAR STRUT

(Continued)

wheel centering is accomplished by a centering cam installed pin extending piston and a centering on the strut through As the strut extends, the wall of the strut. the cam engages pin causing and remain in that the centering the strut to center position until it is compressed again.

Nose

is dampened shimmy out through the use of a friction collar assembly. The friction collar assembly of a consists split collar is attached loaded spring devices, brake to which material. made of brake lining The brake devices bear against portion of inhibiting rapid relative strut outer body thereby the a motion between this ass embly and the gear p.iston, to which the must collars friction This assembly be kept are secured. absolutely free from oil and grease to be effective. (See Page 5-12)

Nose

wheel

.

MAIN GEAR STRUT The main with MIL-H-5606 hydraulicgear strut is serviced servicing instructions, fluid and dry air or nitrogen. For proper and follow the instructions consult Manual the Maintenance very extremely closely servicing important. is strut as proper The

main gear struts incorporate strut contains the a contained portion. in the upper extremely strut operate to is that the gear rotates vation being accomplished by the use and The the gear truss. gear with no adjustments its operation (See Page 5-13).

"floating"

two novel innovations. that allows the fluid

piston This

arrangement

allows

while taxiing. "soft" during retraction.

Another

First,

to be the

innorotation

The of a torque link attached to the mechanical in is entirely system being possible or necessary.

attached Forged landing to the wing spars, gear truss members, drag brace asprovide mounting for main and trunnion the gear The drag brace design incorporates knee sembly. an over-center fitted drag and and downstop. cords brace Rubber bungee to the mechanical down latches. strut as serve gear (See Page 5-14).

5-12

NITROGEN

VALVE

BODY

PIN

UPPER

BEARING

CENTERING

CAM

PISTON

CENTERING ATTACH

COLLAR ASSY

\

ROD

PIN BOLT

'

ORIFICE TUBE DOWN STOP

CENTERING ANTI-SHIMMY FRICTION SHOE

AND PIN

\

\

COLLAR BUSHING

CYLINDER BRACKET ATEEAIGNGPOCY

SCISSORS ASSY

-t'

BE ARING GLAND SNAP

STEERING CYL ATTACH POINT

SCISSOR

RING BUSHING

FORK ASSY

26 4

Nose

Landing

Gear

Strut

5-13

TORQUE

*

LINK SHAFT LOCK BOLT

FILLER

PLUG

THRUST RING

/

RETRACT

TORQUE PIN

/<

TORQUE

'

CYLINDER

LINK

LINK

BUSHING LOCK SCREW

THREADED

CLE VIS

DO NOT REMOVE LOCK SCREW AND CHANGE POSITION OF THREADED BUSHING

SN UBBE R

T HR E A DE DB US HIN G

SRpER IANGN ER

SU HNNNGON SN A P COULDLAR

RING

TORQUE LINK SHAFT

SNUBBER SPRING

MOUNTING PIN

NEEDLE BEARING

UPLOCK

BEARING SPACER

PISTON

BRACKET

OUTER BODY

FLOATING PISTON

BEARING SPACER

BUNGEE YS

'

O '

BUSHING

INNER

'

PISTON

OO SNCL

INN R BHO

UPPER SCISSONæK

NGEN

PLUG

PLUG

VALVE BODY

FELT WIPER

NITROGEN VALVE BODY BOLT

BUSHING BEAp

SPGACER

ORLIFICE

.

RRNG BE RENTAINER

BEEAR NG

FORK

G XLE

WASHER SNAP RING

262

Main

5-14

Landing

Gear

Strut Assembly

ADJUST CYLINDER OVEHTRAVEL TO OBTAIN DRAG BRACE PRELOAD REFER HERE. TO INSTRUCTIONS IN TEXT.

NOTE LEFT GEAR SHOWN RIGHT GEAR OPPOSITE +----MAIN GEAR ACTUATING

CYLINDER

I LANDING

GEAR

TRUSS

'O o

,-

UPPER BRACE

TORQUE LINK HYDRAULIC FILLER

STRUT

TRUNNION BUSHINGS

/ y//

FLUID PLUG

BODY

DRAG BRACE PIN RETAINING BOLTS

----g

e

ADJUST SWITCH BY ROTATING JAMB NUTS

LOWER DRAG BRACE

< '

a

DRAG

GEAR SAFE LIGHT SWITCH

DRAG BRACE PINS ==R

BUNGEES

SCISSORS PISTON

UPLOCK BRACKET FORK ASSEMBLY

AIR VALVE WHEEL

AND BRAKE

ASSEMBLY

-

2625

Main

Landing

Gear

Installation

SECTION FUEL

6

SYSTEM

INTRODUCTION Commander consists in the Model 690 Turbo The fuel system cells, light weight fuel interconnected of twenty-two (22) to form a single tank. The tank has a total volume of 389 U. S. of 384 U. S. gallons. volume The tank is gallons and usable fill located fitted with non-siphoning on the top side type caps of the engine nacelle, of of each wing, outboard and inboard nacelle. fuel right engine From section center the the sump, fuel flows through electric boost pumps and gate type fuel shutoff valves to each engine. FUEL

CELLS

(See Figure

6-1)

of the in the wing outboard The twenty (20) fuel cells located plates of installed fuselage the wing. through access on top are in the center fuel The fuel cell located wing and the fuselage directly cell, which is located proof compartment in a vapor opening below the center wing, through an access are installed The cells are held in place cell compartment. in the fuselage The of snap fasteners cord. and nylon lacing by a combination for Maintenance Manual must be referred Airframe proper to interconnect lacing patterns, tube clamp torque valves and bolt torque valves. FUEL

SUMP

below the lower fuselage fuel cell, The fuel sump is installed 6-2). The in the baggage Figure compartment. (See sump boost pumps, incorporates two two submerged a drain valve, valves and a quantity probe, fuel shutoff measuring are all enclosed in a vapor proof Wing cell sump drains compartment. installed of each lower surface inboard and outboard on the are nacelle. The main sump drain quick is accessible through a release door on the fuselage skin under the right wing. VENT

SYSTEM

for The wing inboard and outboard cells are interconnected from and an atmospheric vent purposes vent line is routed the outboard cell through the lower The exposed wing surface. vent perpendicular line protrudes wing and is vent the tube to the scarfed forward at 45 degrees pressure use to provide a slight siphoning. flight and prevent Fuel vent thermal heaters during if installed equipment, the heaters may be installed as optional will function with the airspeed pitot heaters.

6-1

FUEL

QUANTITY

GAUGE

SYSTEM

light are indicator and a fuel level low warning A fuel quantity provided fuel quantity. The quantity gauging system to indicate of a quantity installed indicator in the right inis comprised installed panel and three fuel quantity strument transmitters wing). in the wing, (center wing, inboard wing and outboard outboard is also installed with the An auxiliary transmitter optional cells. probe long range The variable resistance type of the fuel transmitters jointly measure the density pressure within Maintenance Manual the fuel tank. See the Airframe for component replacement information and fuel quantity gauge calibration The fuel level low warning procedures. system light is actuated by a float switch, and will illuminate at approximately 31 gallons (217 lbs.) fuel remaining.

FUEL

SHUTOFF

VALVE

AND

BOOST

PUMP

fuel shutoff valve is controlled by the Fuel and The electric S/O shutoff valves left switch. Hyd. Emer The are normally Normal switch position, and are closed in the open position, only for ground maintenance and emergency operating conditions requiring supply be fuel fuel off cut at the the to sump. for continuous duty and output presThe fuel boost pump is rated 50 of is about flow. It at PSIG zero turned off and on by sure On" posicontrol switch. It is started at the "Fuel the engine "Air Start" "Ground and operation is continuous and tion the Start" positions of the switch. It is turned off when the engine Off". control switch is placed at "Engine

6-2

16

16

16

EIEEEFUEL EB FUEL

16

SE 20

19

20

20

19

18

1. 2. 3.

4. 5. 6. 7. 8. 9.

10.

OUTBD FUEL CELLS LEFT FWD OUTBD FUEL CELL LEFT AFT OUTBD FUEL CELL LEFT FWD INBD LARGE FUEL LEFT AFT INBD LARGE FUEL LEFT FWD INBD SMALL FUEL LEFT AFT INBD SMALL FUEL CENTER WING FUEL CELL FUSELAGE FUEL CELL RIGHT FWD INBD SMALL FUEL

Figure

11. CELL CELL CELL CELL

12. 13. 14. 15. 16. 17.

18. CELL

6-1. Fuel

19. 20.

System

FUEL FUEL

'

20

19

SUPPLY VENT SYSTEM PRESSURE SHUTOFF VALVE

20

LOOKING AT FUEL

FWD SYSTEM

RIGHT AFT INBD SMALL FUEL CELL RIGHT FWD INBD LARGE FUEL CELL RIGHT AFT INBD LARGE FUEL CELL RIGHT FWD OUTBD FUEL CELL RIGHT AFT OUTBD FUEL CELL FLAP CHECK VALVE FUEL SUMP FUEL PUMPS FUEL QUANTITY TRANSMITTER FUEL FILLER CAP

Schematic

6-3

BOTTOM

OF

FUSELAGE

BOTTOM

CELL

OF

CENTER WING CELL

TRANSMITTER

USEORGE

SUM

TTER

GASKET

FILTER SCREEN

LD PLATE

L

DRAIN FITTING

FUEL LINE ONNECTION

GASKET

F EL ET

SKET

FUEL

DRAIN VALVE ASSY

SHUTOFF VALVE 2555

Figure

6-4

6-2.

Fuel

sump and

Transmitter

Installation

SECTION

ENVIRONMENTAL

CONTROL

7

SYSTEM

Introduction environmental control provides The Turbo system Commander volume flow aircraft large of compressed air cabin, the to a "Bleed Air" for air conditioning and pressurization purposes. routed from the engine through tubing, shut-off compressors, valves and nozzles air flow multiplying motivates jet pumps. created within The resultant low pressure the jet pumps causes with the engine bleed air atmospheric air to combine ambient velocity. Diffusers high flows it at the through jet pumps as end convert high velocity low pressure on the jet pump discharge high pressure air in the cabin compressor air to low velocity is a heat air, which may be up to 500oF, This compressed unit. is routed If cooling is required, air for cabin. the the source and an expansion turbine (air cycle through heat exchangers machine) cabin. before it enters the during manufacture, aircraft cabin is sealed thus it may be tank" that is to be pressurized. of as an The amount of pressure carried in the (air tank) cabin will be proportional air outlet through a controllable to the amount allowed to escape valve). valve outflow air (cabin The

"air

thought

TERMINOLOGY It will be helpful associated with

with to be familiar pressurized aircraft

a.

CABIN pressure

PRESSURE altitude

b.

AMBIENT PRESSURE This is of the cabin, usually tude outside altitude.

and

understand operations.

This is the actual within the cabin. -

-

standard

the actual aircraft

some

terms

altimeter

pressure altimeter

c.

DIFFERENTIAL PRESSURE The absolute difference between aircraft, its in pressurized two pressures, inch difference between cabin the pounds per square altitude altitude. and aircraft pressure pressure

d.

UNPRESSURIZED of a system range equal to ambient

alti-

-

RANGE in which pressure,

-

Refers

the cabin in other

to the operating remains pressure words, no pressuri-

zation.

7-1

TERMINOLOGY e.

ISOBARIC RANGE Refers pressure, to even or constant from the prefix "ISO" meaning derived even or constant, In this pertaining and "BARIC" pressure. to barometric remains altitude regardconstant the cabin pressure range altitude. less of the ambient pressure

f.

RANGE DIFFERENTIAL differential which the cabin altitude and cabin pressure altitude. craft pressure

g.

RATE OF CHANGE change per unit of PER MINUTE".

h.

CABIN ALTITUDE CONTROLLER An instrument designed reference constant pressure to the to provide a selective also incorporates valve. This instrument cabin air outflow control. a cabin rate of change

AIR Refer

7-2

(Continued) -

of operation is a range in remains constant, pressure changes proportional to air-

This

-

Refers to cabin time. It is usually -

pressure expressed

altitude in "FEET

-

CONDITIONING

to Figure

COMPONENT

DESCRIPTION

7-1.

a.

DUCT This duct is designed RAM AIR INTAKE to provide path for ambient air with engine into and mix to enter a bleed air flow through the jet pumps. It also provides a high volume flow through the cooling turbine heat exchanger, This intake duct also interconnects for cooling purposes. with the cabin air ducts, at the "Ram Air" valve.

b.

GROUND BLOWER This D. C. motor exchanger functions air pump heat as a and ground operations.

c.

RAM AIR VALVE A split flapper type check valve located air unit, transition on the as a cabin check valve serves during air conditioning operation, and as a ram air inlet valve when air conditioning is inoperative.

d.

MACHINE AIR CYCLE This unit consists of two parts air and stage exchanger to air heat a two an expansion This cabin cooling device. air It will is the turbine. 26, 000 provide cooling. BTU's of It is important up to lubrication, receive that the turbine shaft bearing proper The vendors at 50, 000 RPM. as the turbine may rotate service instructions must be adhered to.

e.

BLEED AIR SHUT-OFF These VALVES are butterfly by a reversible operated and D. C. motor type valves, integral is required About 15 seconds to open gear train. or close the valve.

-

-

driven during

axial slow

blower flight

-

--

-

-

CONDITIONING

f.

AUTO-TEMP CONTROLLER A D. C. powered transisbalance principle. controller operating torized on the electrical controller Electrical inputs to the are from the temperature cabin temperature and a duct temperature selector, sensor will It selective of provide range temperature sensor. a 600 to 110oF approximately.

g.

ENVIRONMENTAL CONTROL SWITCH A three position, five deck, switch. Detented positions rotary are (1) OFF/RAM, OVERRIDE. and It is used to turn the air (2) AUTO, (3) "Off" "On", and conditioning and select mode of cabin system control. temperature

h.

TEMPERATURE CONTROL VALVE cycle time A 40 second with integral butterfly valve driven by a reversible D. C. motor This modulating valve gear train and travel limit switches. hot used regulate air duct in the primary is compressor to air that bypasses the amount of conditioning the cooling turWhen this valve is full open all incoming bine. air bypasses fully cooling closed all when incoming air flows turbine, the cooling These positions, respectively, through the turbine. two full hot position and full cold position. represent It generally between and provides operates extremes, someTre these two mixture air of hot and cold desired a to give the temperature.

AIR

COMPONENT

(Continued)

AIR

DESCRIPTION -

-

-

CONDITIONING

OPERATION

variations There in engine bleed air control are several meet desired operation of extreme the the requirements to operations well weather and cold weather as as normal -

normal consider switches arrange sub-panel:

Let's first operation, instrument 1.

Environmental

control

2.

Ground

switch

3.

Bleed

4.

Max

select

Flo/Gnd

Start desired When engine on as follows: 1.

Place

2.

Rotate

blower

switch

switch -

-

environmental



OFF/RAM.

ON.

NORMAL.

Cool Switch

select

hot operations.

operations. To place in the system condition, in the following on the pilot's

NORMAL.

-

engine in accordance stabilizes at ground

bleed

to provide

switch

with Flight idle RPM,

to operating

control

switch

Manual procedures. air conditioning turn

engine.

to

-

AUTO.

7-3

AIR 3.

selector Rotate auto-temp incoming air flow at floor

4.

Start

5.

Place

6.

Adjust

Observe (1) GND

Refer

remaining

bleed

engine. select

auto-temp

annunciator COOL, and

to Figure

(Continued)

OPERATION

CONDITIONING

switch selector

position.

to desired outlets). (When

to

-

engine

reaches

(Note

idle

RPM).

NORMAL.

as desired.

panel, the following MAX FLO. (2)

lights

are

extinguished,

7-1.

mode normal of operation the primary jet pump causes air) bleed air now flows valves engine shutoff to open, (bleed Ambient through the jet pumps and into the primary compressor. ratio 1:1 about mixes with bleed air air in the jet pumps at a to provide air flow into the cabin for air conditioning a high volume and pressurization. The primary air temperature compressor moderate is very at (less than 200oF) when engines are operating Primary air temperature will ground idle power. compressor when engines 4000F, increase at to approximately are operated will have control Thus, system the temperature takeoff power. air through the cooling turbine to to divert some of this incoming from becoming keep the cabin temperature too hot, even in moderately most, cold weather. if not all, of the In hot weather cooling incoming air is routed through the turbine until the cabin valve modulates control down, is cooled then the temperature to variable mixing mode. air some

This

fumes is entering the cabin, the "BLEED or smoke might be used determine which engine switch be may to desired To isolate, place bleed select engine, switch the source. to engine this will cause the jet pump shutoff valve on the opposite minute close, isolating engine. Allow least for the at that to one condition If bleed change. condition persists, place select to switch clears, engine, if condition continue operation to opposite isolated. with faulty If condition doesn't system improve, use Flight Manual approved procedures. If an in-flight emergency shutdown engine becomes the bleed select switch should necessary, feathered be used to isolate engine. the If noxious SELECT"

extremely operation, under cold condition, usually Max Flo encountered cabin begin cool. This is at high altitude, may the to has reached its limit and system that the normal an indication enough heat isn't available. Placing there just the "DIRECT energy BLEED/AUX JET PUMP" switch will control to Max Flo cause the auxiliary jet pump valve to open to supplement the primary jet The additional hot air input will meet rethe cabin heating pumps. for condition quirements When the auxiliary stated. jet pump valve

7-4

AIR

CONDITIONING

OPERATION

(Continued)

in the light will be illuminated is not closed, the "Max Flo The Max Flo selection annunciator panel. can be used during recommended either However, ground or flight operations. for optimum Manual procedures should be followed Flight perand operations. formance

"

implies, is as the name a mode of operamethod of cooling down a expeditious Its use is limited heat soaked cabin in hot weather. to ground below 90% RPM. To gain access operations and engine operations COOL" first select normal air conditioning mode, to "GROUND as outlined, below 80% RPM, previously place then with engines "DIRECT BLEED/AUX control switch JET PUMP' to Ground Cool This selection and auto-temp switch the primary causes to cool. jet pump valves to close and the direct bleed valve to open, thus undiluted direct engine bleed air enters the primary compressor. close to isolate (Air check valves the inlet on the jet pump outlets This high temperature direct bleed air drives air duct). the performance cooling maximum and will turbine at approximately approximately cooling provide 26, 000 BTU/HR. air flow to the cabin. Cooling air is ducted turbine discharge to the cabin overhead "GASPERS" floor ducts. When the as well as to the under valve bleed is not fully closed, direct the "Gnd Cool" light will panel. illuminate in the annunciator Ground

Cool

tion to provide

In warm

operation

the

most

humid weather system the air conditioning with smoke do not confuse in the cabin with the temperature temperature a warmer

"fogging" select

-

-

may cause if this occurs, control system.

should rotate fail to function, If the auto-temp control system the selection. environmental control switch The to "OVERRIDE" regulated by toggling the cabin temperature can then be manually "HOT -COLD" override switch Should temperature as required. he may at his discretion the pilot so desire, use manual temperacontrol, by positioning in lieu of automatic the environture control mental control switch selection, and toggle the HOT / to override COLD selector switch and maintain to establish as required desired cabin temperature.

7-5

PRESSURIZATION

COMPONENT

DESCRIPTION

outCABIN PRESSURE CONTROLLER The cabin air pressure controlling controller flow valve contains pressure two separate variable isobaric, and selective rate of change. systems; pressure cabin altitude, is used to select desired and This controller cabin climb and descent rate of change. schedule -

OPERATION

(See Figure

-

7-2

).

atmosphere condition, enters the controller through chamber air orifice and filter, and rate the reference If the cabin altitude selection is greater pressures are equal. bellows is compressed than field altitude, the isobaric (by spring force) metering valve opens. During and the isobaric take-off if the aircraft rate of climb exceeds rate, the cabin selected reference chamber is reduced, resulting in a pressure pressure because differential the rate diaphragm the rate metering across valve position limits in rate chamber The the reduction pressure. valve tometering rate control diaphragm then moves the isobaric ward close to limit the flow of air from the cabin reference chamber. The outflow valve reacts to the rate of change of reference pressure which controls During descent the rate of change of cabin pressure. if the resultant in cabin reference exceeds rate of increase pressure diaphragm the isobaric the selected rate, the rate control moves air from the valve (toward open) to a metering position and more valve reference The outflow chamber is bypassed to atmosphere. in reacts pressure to limit the rate of increase to the reference cabin pressure. In a static

the cabin

As the cabin

approaches altitude, bellows the isobaric the selected valve expands sufficiently control of the isobaric metering to assume The isoas the rate and cabin reference are equalized. pressures baric reference control system now maintains pressure, a constant reference in the outflow valve remains and variconstant pressure air inflow ations in compressed to the cabin acts direct ly to position altitude. controlling cabin pressure at the selected the outflow valve, 7-3 ). The valve contains (See Figure a control reference chamber, valve, diaphragm and poppet poppet pressure dump/reference sensing return static port, spring, pressure sense differential relief valve. The poppet port and a calibrated pressure negative cabin differential return spring limits to approxipressure mately 0. 25 P. S. I. D. The positive cabin differential relief valve P.S.I.D. is set at 5.2 + located There are two of these valves bulkhead. The two valves on cabin forwird pressure are pneumatically interconnected to act in unison, or as one.

OUTFLOW

VALVE

-

.1

SOLENOID OPERATED DUMP VALVE (See Figure valve interconnects controller, to the cabin pressure (dump) source and the outflow safety valves. vacuum is energized controller is rendered the cabin pressure -

7-6

7- 4 ). This instrument When the solenoid inoperative,

PRESSURIZATION

COMPONENT

DESCRIPTION

(Continued)

is vented and a vacuum pressure to the outflow valves reference chamber, this action causes the valves to unseat to dump cabin cabin pressurization. to prevent pressure or, if unpressurized, by means switch of a cabin depress The solenoid is energized switch mounted on left main landing or ground contact gear scissor link. When the solenoid is de-energized is pressure vacuum removed from the control system and the outflow valves are referenced controller. to the cabin pressure CABIN PRESSURE CONTROL SYSTEM OPERATION After Before engine is turned on. start cabin air conditioning take-off and cabin rate control set cabin altitude (1) For as follows of 27, 000 feet or less, flight plan altitudes set cabin pressure controller by rotating the, cabin altitude to flight plan altitude until desired aligns with index knob clockwise flight plan altitude pointer. (2) For flights above 27, 000 feet, select a 10, 000 feet controller. cabin altitude with the cabin pressure Utilizing this 27, 000 feet would be method all operations above approximately differential maximum basis. pressure on a constant (3) Set cabin rate control rate for take-off and after take-off, to minimum cabin rate proportional readjust rate schedule to actual aircraft of climb. This should provide that would cause the a schedule slightly cabin to reach planned before altitude or at the same time altitude. The following reaches planned formula the aircraft may cabin rate schedule: be used as a guide in determining -

-

Cabin

Aircraft

Change-Thousands Change-Thousands

Feet Feet

X Aircraft

Rate

of Climb=Cabin

Rate

and landing, For descent in the controller set cabin altitude to NOTE: landing and set cabin rate as required. pattern altitude, comfort cabin rate of climb should be no For passenger or descent greater than what is necessary to cause the cabin to reach planned altitude reaches slightly ahead of or at the same time the aircraft altitude. the planned

7-7

CABIN AIR ORIFICE

WITH

FILTER

ATMOSPHERE PRESSURE SENSING CONNECTION

VALVE OUTFLOW CONNECTION

RATE CHAMBER AIR FILTER

REFERENCE

CHAMBER ISOBARIC METERING VALVE

RATE CONTROL DPRING CAPILLARY

RATE CONTROL DIAPHRAGM

TUBE-

AOLŒR

RATE CHAMBER

TION

SPRING

Ë'TEERC AMB RVE

AOLŒRRACTION

L RATE

SELECTOR

SCREW

KNOB

CABIN ALTITUDE SELECTOR KNOB

CABIN ALTITUDE

POINTER ISOBARIC CONTROL

Figure

7-10

7-2

Cabin

Pressure

Controller

Schematic

BELLOWS

STA. 5. 5 BULKHEAD OUTFLOW VALVE DIAPHRAGM (ACTUATOR PORTION)

I i

REFERENCE CHAMBER

BASE ASSY POPPET VALVE

OUTFLOW

OUTFLOW VALVE COVER PLATE

PLUG

POPPET VALVE RETURN SPRING

-

ADJUSTING SCREW CHECK NUT ADJUSTING SCREW

:

STATIC PRESSURE i

DUMP

do

OUTFLOW GUIDE

CONNECTION

BAFFLE

TO CONTROLLER

VALVE PLATE

OUTFLOW

VALVE

PILOT HEAD

OUTFLOW VALVE

ASSY

DIAPHRAGM

(VACUUM RELIEF AND BALANCE PORTION) AMBIENT REFERENCE

PRESSURE PRESSURE

CABIN PRESSURE

Figure

7-3

Outflow

Valve

Schematic

7-11

SAFETY-OUTFLOW VALVE

FWD PRESSURE

BULKHEAD SAFETY-OUTFLOW VALVE

STATIC AIR (SEE NOTE)

--

STAATICCPORRT STATIC

AIR

STATIC

PORT

REF CHAMBER PORTS THORENE-WAY SOLE

VACUUM

OID

SOURCE

CABIN PRESSURE CONTROLLER

EFFECTIVE A C 11121 AND SUBS

OUTFLOW PORT

MAX FLO

N

GROUND

GND COOL

INTERNAL

CHECK

CONTACT

FILTER)

STATlc PORT

VALVE

ENVIRONMENTAL 00FO

AUTOTEMP

ovaan

stansa

0 0E WARM

¢OOL

RATE A

NOR

L

CAABIN

COOL GND (0DL PRESSUWilATl0R ROT PERMlTTED ouRING TAKEOFF AND LARolNG

NOTE

CABIN PRESSURE CONTROLLER

STATIC SOURCE FOR CONTROLLER IS LOCATED ON 5.5 PRESSURE BULKHEAD

Figure Cabin

7-12

Pressure

Control

Schematic

7-4

t

a

oommo

le

7-13

a

13

14

12

11

10

9

8

29

27

23

25

21

19

17

6

7

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5

13

15

4

11

3

9

2

7

5

3

-40,000 --

35,000

-

3C, COO

I

\

|

\

ll \\

|

\

|

\

IIIlill llIIll!\

\

\

\

\ \

\ \

\ \

\ \

\

ll

ll

I

I

I I I II llllml M I MI IW1\\\l

¯

¯

¯¯

20, 000

15, 000

10,000

¯ -

--

-5,

000

SL.

5

10

15 AIRCRAFT

ALTITUDE--THOUSAND

20

25

FEET

30

35

40

50

( J

SECTION MISCELLANEOUS

8 SYSTEMS

SYSTEM

VACUUM

provides instrument system vacuum vacuum a filtered instruments, of the air operated for operation source aircraft engine is operating. when either Vacuum is obtained The air ejector has from the venturi port of an air ejector. by pressure regulated engine and is powered parts no moving bleed air. Air flow through the ejector creates a high vacuum at the venturi This high vacuum is then regulated port. to deSee Figure sired valve for the instrument No. 1. system. The

(suction)

BLEED

AIR PRESSURE

REGULATOR

located The bleed air pressure behind regulator, the rear wing used to restrict is a mechanical poppet type regulator spar, An interthe bleed pressure (30-150 psig) down to 18+ 1 psig. nal relief valve should regulator fail, protects the the system A cockpit by limiting instrument 21+ 1 psig. the pressure to indicates at the inlet to the vacuum the regulated pressure 18 and 19 ejector. The instrument has a green are between normal yellow 19 between psig indicating and are pressure a is operating and 22 psig indicating that the regulator on the relief setting.

VACUUM

EJECTOR

containaluminum assembly is a forged ejector venturi chamber. mixing Air and passes a a into the throat of the venturi thereby creating through the nozzle Ports connect this area to the vacuum area. a low pressure it is directed After the air passes system. through the venturi value where its velocity is reduced to the diffuser to a suitable The air is exhausted for exhausting through to the atmosphere. side of the fuselage below the wing. an opening on the right The vacuum ing a nozzle,

VACUUM

RELIEF

VALVE

valve relief is adjusted The vacuum the vacuum to maintain being 3.8 and 5.0 inches level at between Hg. The usual value periodiThe poly-foam 5. O inches Hg. type filter is cleaned operation. cally in soap and water improper system to prevent

8-1

VACUUM

INSTRUMENT

SYSTEM

The inlets instruments together to the vacuum are manifold and are connected located in the compartfilter to a common Restrictor ment on the right side of the nose wheel well. valves installed bank and adjacent indicators to the turn are 2. inches reduce Hg. 1 the vacuum to them to to DE-ICER

SYSTEM

BOOT

boots edges of de-icer to the leading are bonded and empennage. controls disAn electric timer a valve, located behind the rear wing spar, which directs or pressure to the boots as required vacuum

Pneumatic the wing

tributor either

for system

operation.

valve is in the normally closed position boots deflating and holding is directed them to the edges. When the boots them against the leading are cycled "ON" an electric valve solenoid position the moves to a and directs from the turning "OFF" the vacuum pressure bleed regulator boots. air pressure to the When vacuum

the distributor

STATIC

SYSTEM

side of the aft fuselage on either are located horizontal stabilizer Plumbing edge. leading the is routed from the static ports up to the top of the aft fuselage beside the then forward and down to a static drain port located Plumbing right rudder co-pilots pedal. is then routed up to instruments. It is imperative the various that the static system of cabin be absolutely into the leakage pressure as any secure affect would of flight seriously instrusystem the accuracy the alternate with a heated The aircraft is also equipped ments. head located side of the forward static source on the right Two

static

forward

ports

of

fuselage. OXYGEN The

SYSTEM

of a 22 cu. ft. bottle is composed located manual regulator located compartment, on the a co-pilots side panel, When and built-in boxes. face mask storage mask box mask is opened, will drop and out when storage the the pin is pulled, continuous flow oxygen is available. the lanyard

system

oxygen

in the baggage

OXYGEN

STORAGE

The 22 cu. ft. ward bulkhead

8-2

CYLINDER

storage oxygen of the baggage

cylinder is mounted on the forcompartment and is removed for

OXYGEN

STORAGE

CYLINDER

(Continued)

filling. The oxygen supply valve must be turned on prior valve is flight as access gained through the baggage to the compartment.

OXYGEN

to

REGULATOR

is mounted The Scott oxygen regulator panel. Two gauges and an adjustment the regulator to be used in regulating operation. A pressure gauge indicates regulator is adjusted. the

side on the co-pilots knob are provided on and monitoring system the altitude to which

knob To operate the system the pilot rotates the regulator until the altitude corresponds with indicated the on the gauge existing cabin altitude. Oxygen is delivered in a continuous flow to the user in an amount with the existing commensurate cabin altitude.

FIRE

DETECTOR

SYSTEM

radially around Three (3) Fenwall thermo-switches are located normally engine firewall. The contacts thermo-switch the are Should the temperature rise. open and close on a temperature surrounding rise above a preany one of the thermo-switches value, close and turn on a fire determined the switch contacts panel. light in the annunciator warning

WINDSHIELDS

HEATED

electrically heated The aircraft is equipped with glass laminate windshields. include high and low heat Electrical components felays located in the right side of the fuselage nose section controllers located and automatic on the right temperature bulkhead side of cabin aft pressure (fuselage station 178). The electrical 1 through 5 terminals on windshields are numbered and terminal 3 is ground. At normal the room temperature, low heat element 1. 24 ohms (terminal 5 and 3) should read + 15% and high heat element (terminal 4 and 3) should read 799 ohms + 15%, terminals 1 and 2 are for the temperature 310 ohms + 3. There and at 700F should measure sensor are repairs field adjustments permitted no or on tEe temperature controllers. -

-

-

-

RUDDER

ANTI-ICING

SYSTEM

consists electric heated This system of three separate slot has two heater elements, The rudder one mounted rudder horn rib and one mounted side of on the upper

elements. on the the antenna

8-3

(Continued)

SYSTEM

RUDDER

ANTI-ICING

housing. horn. If

The third element is located on the rudder elements, in the heating trouble is suspected be made.

check of each element sistance should check: should meet the following Trim

tab horn

element

Upper

rudder

slot

Lower

rudder

slot

2. 32

3.18 -

+

0.05

forward aft leads

-

8-4

a reElements

2. 72 ohms. ohms.

leads 3. 25

of the rudder Operation slot heat system Flight Manual procedures. Airplane

with

trim tab

1. 64 + 0.05 0. 05~ohms.

ohms

.

+

must

be in accordance

l

VACUUM FILTER ATTITUDE

AIR

GYRO VACUUM MANIFOLD

TURN & BANK INDICATOR

VACUUM GAGE

VACUUM CONTROL VALVE

DIRECTIONAL

GYRO

y

,

INSTRUMENT VACUUM MANIFOLD

LEFT ENGINE

RIGHT ENGINE

VACUUM RELIEF VALVE

PRESSURE REGULATOR AND RELIEF VALVE TO REGULATED GAGE PRESSURE

EJECTOR PUMP

//)

CHECK

,

EXHAUST

VALVE

BLEED

AIR LINE

BLEED AIR PRESSURE

TO ENVIRONMENTAL SYSTEM (REF)

VACUUM 288

Vacuum

System

Schematic

8-5

INSTRUMENT

PANELS

OVERHEAD

SWITCH PANEL

BOOTS ONECY

PRESSURE GAGE

MAN

LEFT WING DEICER BOOT

RIGHT WING

TIMER LEFT ENGINE

RIGHT ENGINE FROM VACUUM INSTRUMENTS

,,

PRESSURE REGULATOR

FUSELAGE

/

SKIN

/

AIR EJECTOR

i

DISTRIBUTOR VALVE

CHECK VALVE

TO JET BLEED

EMPENNAGE DEICER BOOTS

PUMPS

AIR

REGULATED

PRESSURE

SUCTION

----

REGULATED

PRESSURE

ELECTRICAL

ACTUATION

AND SUCTION

Wing

8-6

R211

and

Empennage

Deicer

System

Schematic

20

COPILOT'S OUTLET

OXYGEN REGULATOR

PASSENGER (TYP) OUTLETS

OXYGEN SUPPLY

¯

PILOT'S OUTLET

OXYGEN MASK

FLOW INDICATOR RED TO GREEN R211

Figure

9-10.

Oxygen

System

8-7

9

CHECK

Make Inc. Break

Make Inc. Break

3/O PSI PSI

Dec·25o

Dec.

75 PSI

'*"CHCONNECTION

IVE TO O

NEG

60 PSI

VALVE

SWITCH

CONNECTION

UNPEATHERING PUMP CONNICTION

NEGATIVE yogogg CHECKOUT

-i---------Ei---------Illi MP

CLOSED)

CASE

NEGATIVE

1

MALY .

CHECK g VALVI E

TOROUE SEN50R PRESSURE

REGULATOR

FILTERED ENGINE OIL

SSURE \ DUMP

RESET PISTON

CHECK VALVE

MIN SPEED STOP

DUMP

CAM

su

TO UE INSOR PMSSURE

UM

5E

AIN mÕ!

o TORSION u

-

-

SE

HYDRAULIC

5HAFT

Rotot

ULATOR

-

-

D

RAW

SHAFT -

SPEED CONTROL LEVER COORDINATED WITH SPEED SETTING LEVER SHAFT

TOROUS SIGNAL HIGH FRESSURE RELIEF VALVE

TORQUE

SENSING SE CT10N

CASE

ZEROASLOPE ,,,,,,,,,,,^¿UMMENT

--8-851

r

-ELECTRIC PRESSURE TRANSDUCER PAD

-lilli-5

Mililil-Illililim

--

-

DUMP

MANUAL PROP FEATHER

CASE

DIFFERENTIALPRESSURE TRAN5DUCER

PROPELLER GOVERNOR r

PROPELLER SERVO PO$lTIONING

--

PliTON

Elisillii

1-5

Ilillipas---Hiiiinliinill---

-

(NOT FURNISHED) .

. /



TOROUE VALVE

.

.

.

SENSOR

FEATHERINC VALVE

PROPELLER OIL FLOW TUBE



FEATMit

e

-NEGATIVE LOCKOUT

.

/

s

PROPELL ER ONCHROL

I

DIBECTION ,

C

& ---me

-

-

a-aPITCH CONTROL LEVER COORDINATED WITH POWER SETTING SHAFT

Figure

COCKPIT POWER LEVER CONNICilON

4

9

4-33 4-34

CAVENGE

OIL

OIL-FUEL HE A T EXCHANGER

f.'"JPENEED

FLIGHT

--

TNIN

IDLE FLOW ADJ

INCREASE -POWER SEHA TMG

NCREÅ5E

BODY VENT

FU EL CONT ROL

PROPELLER PITCH CONTROL LEVER CONNECTION

ANL EICINC

:'N

E

THERMOSTAT

FUEL PUMP

ON

R START

FUEL F ILT ER

RD

FLOW

ADJ

OW ::CHMENT-

--

OO

METERING VALVE

PROPELLER GOVERNOR SPEED CONTROL LEVER CONNECTION

MIN FLOW ADJ

FUEL INLEy-

OVERSPEED GOVERNOR

.MPSOOST (INJE h

55URE FILTER VALVE

VANE TYPE)

BYPA

-HIGH PRESSURE RELIEF VALVE



-

MAXW ESSEURIZING

CHMENT

STOP OVERBOARD

o

.

L

oDERR

DRAIN --

OVERSPEED

---

Psa

ARD

TO ATMOSPHERE

EXHAUST

--

Li

EUE MO

..

PASS

R

¯¯

iiiii

INLET VISCO ........

FLOW DIVIDE A ND DRAIN VALVE

.

......

...

....-.\..

4-13 4-14

A

FLOW DIVIDER VALVE OVERBOARD

-R

-

-

'MANIF OR41N

4

TURBINE PLENUM DRAIN VALVE

/

/

L FUEL

=

FUEL SHUT OFF VALVE

Figure

TEMPERATURE SENSOR

INLET

FLOW METER

DRAIN

JET

ANTI-ICINC VA LVE

L



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